SA
Uploaded bySaif al-din ali
416 views

Nozzles

1. The document discusses experiments performed on converging and converging-diverging nozzles. 2. Converging nozzles accelerate fluid flow to supersonic speeds at the nozzle exit, while converging-diverging nozzles can accelerate fluids to both subsonic and supersonic regimes depending on pressure ratios. 3. Calculations are shown for mass flow rates through a nozzle at different pressure ratios using theoretical equations.

Embed presentation

Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 1 | P a g e [power plant Laboratory II] University of Baghdad Name: - Saif Al-din Ali -B-
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 2 | P a g e TABLE OF CONTENTS Objective............................................................................I INTRODUCTION.............................................................II THEORY.........................................................................III Calculations and results..................................................V DISCUSSION..................................................................VI
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 3 | P a g e Experiment Name:- 1. Objective 2. Introduction Two types of nozzles: - 1. Converging-Diverging or " De Laval" Nozzles have been widely used over the last few decades in many engineering contexts, from civil and mechanical to aerospace uses. They are designed to accelerate fluids to supersonic speeds at the nozzle exit. Nearly all rockets make use of this fact to create an effective propulsion system to reach high velocities. Whilst their operation is of a simple appearance, the combination of flows reached, be that subsonic and supersonic and the subsequent change of properties such as pressure, density and temperature make the underlying investigation of their performance more complicated than first expected. Their operation relies on the ratio between the inlet stagnation pressure P0 and outlet back pressure Pb. As this ratio Pb/Po is brought down from unity, the mass flow rate increases till a maximum value is achieved where the Mach number in the throat (see Figure 1) becomes sonic. ( Mach no = 1). This is referred to as "Choked flow". As the ratio is further decreased the flow becomes supersonic in the diverging nozzle, till the design pressure ratio is achieved (0.53 for air) with supersonic flow occurring at the nozzle exit. After this the flow becomes more complicated and normal and oblique shock waves begin to occur inside and outside of the nozzle respectively. The Purpose of this report is to gain an understanding of the nature of this flow by investigating the pressure ratios effects on the mass flow rate of air through the system and the differing pressure distributions that occur at varying lengths into the nozzle. Figure 1. Schematic of a converging-diverging nozzle 2. converging nozzle
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 4 | P a g e Converging nozzles, as shown in Figure 2, are tubes with an area that decreases from the nozzle entry to the exit (or throat) of the nozzle. As the nozzle area decreases, the flow velocity increases, with the maximum flow velocity occurring at the nozzle throat. As the inlet flow velocity is increased, flow velocity at the nozzle throat keeps increasing until it reaches Mach 1. At this point, the flow at the throat gets choked, meaning that any further increase of inlet flow velocity will not increase the flow velocity at the throat. It is for this reason that converging nozzles are used to accelerate fluids in the subsonic flow regime alone and can commonly be found on all commercial jets (except for the Concord) as they travel at subsonic speeds. Figure 2. Schematic of a converging nozzle 3. divergent nozzle represents a divergent nozzle for a fluid whose peculiarity is that — decreases with the drop of pressure, i.e., specific volume increases at a faster rate than velocity with the drop of pressure. The area of cross-section should increase as the pressure decreases. Figure 3. diverging nozzle the flow conditions that can be observed in a converging nozzle: 1. No flow condition, where the back-pressure is equal to the total pressure. 2. Subsonic flow, where the flow accelerates as area decreases, and the pressure drops. 3. Subsonic flow, where there is significantly higher acceleration and the pressure drops. 4. Choked flow, where any pressure drop does not accelerate the flow. 5. Choked flow, where the flow expands after the nozzle exit (considered non- isentropic).
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 5 | P a g e Figure 4. Flow conditions and regimes in a converging nozzle (theoretical predictions) converging-diverging nozzle shows the following seven profiles in the position versus pressure ratio plot. Note that the first vertical dashed line on the left of the p/pO versus distance along the nozzle plot is the location of the throat, the second vertical dashed line is the location of the nozzle exit, and the horizontal dashed line marks the choked condition. 1. Subsonic flow that never reaches choked condition. 2. Subsonic flow that reaches choked condition but does not attain supersonic velocities (considered isentropic). 3. Subsonic flow that reaches choked condition, with the resulting supersonic flow forming a normal shock, which then experiences subsonic deceleration. Here, the normal shock causes a sudden drop in velocity and an increase in back-pressure, as indicated by the sudden increase in p/pO. 4. Subsonic flow that reaches choked condition, with the resulting supersonic flow forming a normal shock after the nozzle (considered isentropic in the nozzle). 5. Over-expanded flow – the pressure at the nozzle exit is lower than the ambient pressure, causing the jet exiting the nozzle to be highly unstable with huge variations in pressure and velocity as it travels downstream. 6. Flow after the choked condition is supersonic through the nozzle, and no shock is formed. 7. Under-expanded flow – the pressure at the nozzle exit is higher than the ambient pressure and results in similar effects as over-expanded flow. Figure 5. Flow conditions and regimes in a converging-diverging nozzle (theoretical predictions) 3. Theory
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 6 | P a g e The characteristic of a nozzle can be graphically represented by diagram which shows the mass flow rate through the nozzle related to the downstream pressure outlet, with fluid conditions maintained constant upstream of the nozzle. In subsonic nozzle conditions the flow rate can be expressed by: 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑨 𝒖 = 𝝅 𝟒 𝑫 𝒕𝒉 𝟐 Where: Po = Total pressures upstream the nozzle, Vo=Specific volume upstream the nozzle Au= the narrow outlet section of the nozzle (throat). P2 = Pressure downstream the nozzle, K = Specific heat ratio (taken l for temperature 170 ° C) For critical pressure downstream the nozzle the mass flow rate will be max (i.e.) the nozzle is chocked can be calculated as: 𝑸 𝒎 𝒂𝒙 = 𝑨 𝒖 𝒑 𝟎 √ 𝒑 𝟎 𝝂 𝟎 ∗ √ 𝟐𝒌 𝒌 − 𝟏 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 7 | P a g e 4. Calculations and results 𝑨 𝒖 = 𝝅 𝟒 𝑫 𝒕𝒉 𝟐 = ( 3.14 4 ) ∗ (8 ∗ 10−3)2 = 5.03 ∗ 10−5 𝑚2 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 𝟎. 𝟎𝟑𝟏𝟏𝟐𝟏𝟖 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟗𝟏.𝟐 𝟎.𝟒𝟔𝟒𝟐𝟓 = 𝟎. 𝟎𝟕𝟖𝟔𝟗𝟗 𝒎 𝟑 𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟑. 𝟓 = 1.142857143 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.03950456 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟏.𝟔 𝟎.𝟒𝟔𝟒𝟐𝟓 = 0.090874 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟑 = 1.333333333
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 8 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟐. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟐. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.042527341 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟒𝟒.𝟒 𝟎.𝟒𝟔𝟒𝟐𝟓 = 0.099027755 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟐. 𝟓 = 1.6 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎∗𝒗 ∗ √ 𝟐𝒌 𝒌−𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟐 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟐 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.041861669 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟓𝟐 𝟎.𝟒𝟔𝟒𝟐𝟓 = 0.101600333 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟐 = 2
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 9 | P a g e 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟒. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟒. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.035414399 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟏.𝟔 𝟎.𝟑𝟕𝟐𝟗 = 0.101395891 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟒. 𝟓 = 1.11111 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟒 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟒 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.04612388 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟓𝟗.𝟔 𝟎.𝟑𝟕𝟐𝟗 = 0.116163587 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟒 = 1.25
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 10 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.051420707 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟖𝟐.𝟒 𝟎.𝟑𝟕𝟐𝟗 = 0.124184098𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟑. 𝟓 = 1.428571429 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.053222816𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟗𝟕.𝟔 𝟎.𝟑𝟕𝟐𝟗 = 0.129254907 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟑 = 1.666666667
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 11 | P a g e 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.03500503 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟕𝟓 𝟎.𝟑𝟐𝟏𝟐 = 0.085801054𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟓. 𝟔 = 1.071428571 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟒 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟒 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.041800254 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟗𝟎 𝟎.𝟑𝟐𝟏𝟐 = 0.093990346 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟓. 𝟒 = 1.111111111
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 12 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟏 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟏 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.049192115 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟓 𝟎.𝟑𝟐𝟏𝟐 = 0.110768685𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟓. 𝟏 = 1.176470588 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟒. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟒. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.052882165𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟒𝟓 𝟎.𝟑𝟐𝟏𝟐 = 0.119301525𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟒. 𝟗 = 1.224489796
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 13 | P a g e 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟔. 𝟓 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟔. 𝟓 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.03500503 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟕𝟓 𝟎.𝟐𝟕𝟓𝟐 = 0.092687731 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟔. 𝟓 = 1.076923077 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟔. 𝟐 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟔. 𝟐 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.051562331 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟗𝟎 𝟎.𝟐𝟕𝟓𝟐 = 0.101534322𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟔. 𝟐 = 1.129032258
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 14 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.05840326 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟓 𝟎.𝟐𝟕𝟓𝟐 = 0.119659346 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟓. 𝟗 = 1.186440678 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.063522547 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟒𝟓 𝟎.𝟐𝟕𝟓𝟐 = 0.12887706 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟓. 𝟔 = 1.25
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 15 | P a g e Experimental 1 state Po bar Pb (bar) To ( c) ∆P (mmHg) Tb Vo (m3/kg) 1 3 2.5 145 0.12 137 0.464 2 3 2 145 0.16 130 0.464 3 3 1.5 145 0.19 125 0.464 4 3 1 145 0.2 120 0.464 2 1 4 3.5 150 0.16 144 0.3729 2 4 3 150 0.21 132.5 0.3729 3 4 2.5 150 0.24 132 0.3729 4 4 2 150 0.26 130 0.3729 Theoretical 1 1 5 4.6 165 75 0.3212 2 5 4.4 165 90 0.3212 3 5 4.1 165 125 0.3212 4 5 3.9 165 145 0.3212 2 1 6 5.5 168 75 0.275 2 6 5.2 168 90 0.2752 3 6 4.9 168 125 0.2752 4 6 4.6 168 145 0.2752
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 16 | P a g e Experimental Q_exp R Q_th 1 0.078699279 1.142857143 0.031121877 0.0908741 1.333333333 0.039504565 0.099027755 1.6 0.042527341 0.101600333 2 0.041861669 2 0.101395891 1.111111111 0.035414399 0.116163587 1.25 0.04612388 0.124184098 1.428571429 0.051420707 0.129254907 1.666666667 0.053222816 Theoretical 1 0.085801054 1.071428571 0.03500503 0.093990346 1.111111111 0.041800254 0.110768685 1.176470588 0.049192115 0.119301525 1.224489796 0.052882165 2 0.092687731 1.076923077 0.042127888 0.101534322 1.129032258 0.051562331 0.119659346 1.186440678 0.05840326 0.12887706 1.25 0.063522547 Experimental 1 ∆P*760 Pb (bar) +1 Po bar +1 91.2 3.5 4 121.6 3 4 144.4 2.5 4 152 2 4 2 121.6 4.5 5 159.6 4 5 182.4 3.5 5 197.6 3 5 Theoretical 1 75 5.6 6 90 5.4 6 125 5.1 6 145 4.9 6 2 75 6.5 7 90 6.2 7 125 5.9 7 145 5.6 7
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 17 | P a g e 5. DISCUSSION 1. 0 0.02 0.04 0.06 0.08 0.1 0.12 0 0.5 1 1.5 2 2.5 Q R Experimental 1 Q_exp Q_th 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0 0.5 1 1.5 2 Q R Experimental 2 Q_exp Q_th
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 18 | P a g e In all the drawings, it turns out that the condition is direct and the pitch of the gradient varies depending on the situation 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 1.05 1.1 1.15 1.2 1.25 Q R Theoretical 1 Q_exp Q_th 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 1.05 1.1 1.15 1.2 1.25 1.3 Q R Theoretical 2 Q_exp Q_th
Saif al-din ali Madi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 19 | P a g e What is the effect of the downstream pressure nozzle on the flow rate values? It has great influence on the amount of outflow and the type of flow as per the drawing

More Related Content

PDF
Performance of the four strokes diesel engine
bySaif al-din ali
 
PDF
Pressure distribution along convergent- divergent Nozzle
bySaif al-din ali
 
PDF
Characteristics of a simply converging nozzle through which steam is passes
bySaif al-din ali
 
PDF
Water cross flow shell and tube heat exchanger | Heat Transfer Laboratory
bySaif al-din ali
 
PDF
Pressure distribution around a circular cylinder bodies | Fluid Laboratory
bySaif al-din ali
 
PDF
Refrigeration air conditioning laboratory Moist Air Properties and Air-Condi...
bySaif al-din ali
 
PDF
Deflection of curved beam |Strength of Material Laboratory
bySaif al-din ali
 
PDF
performance of the four strokes diesel engine
bySaif al-din ali
 
Performance of the four strokes diesel engine
bySaif al-din ali
 
Pressure distribution along convergent- divergent Nozzle
bySaif al-din ali
 
Characteristics of a simply converging nozzle through which steam is passes
bySaif al-din ali
 
Water cross flow shell and tube heat exchanger | Heat Transfer Laboratory
bySaif al-din ali
 
Pressure distribution around a circular cylinder bodies | Fluid Laboratory
bySaif al-din ali
 
Refrigeration air conditioning laboratory Moist Air Properties and Air-Condi...
bySaif al-din ali
 
Deflection of curved beam |Strength of Material Laboratory
bySaif al-din ali
 
performance of the four strokes diesel engine
bySaif al-din ali
 

What's hot

PDF
Evaluation of thermal performance of a typical vapor compression refrigeratio...
bySaif al-din ali
 
PDF
Using the convergent steam nozzle type in the entrance
bySaif al-din ali
 
PDF
Flow system control
bySaif al-din ali
 
PDF
Pipe insulation efficiency study unit |HEAT TRANSFER Laboratory
bySaif al-din ali
 
PDF
Flow system control
bySaif al-din ali
 
PDF
Fluid Laboratory | Centrifugal fan
bySaif al-din ali
 
PDF
Free heat convection |HEAT TRANSFER Laboratory
bySaif al-din ali
 
PDF
Induced flow | Fluid Laboratory | U.O.B
bySaif al-din ali
 
PDF
forced heat convection | HEAT TRANSFER Laboratory
bySaif al-din ali
 
PDF
Aircraft propulsion axial flow compressors off design performance
byAnurak Atthasit
 
PDF
Axial compressor theory - stage-by-stage approach - 28th January 2010
byCangTo Cheah
 
PDF
Predicting Performance Curves of Centrifugal Pumps in the Absence of OEM Data
byVijay Sarathy
 
PDF
Minor losses valve
byMuhammed Fuad Al-Barznji
 
PDF
Experimental radial tipped centrifugal fan
byC.Cesar Nascimento
 
PDF
Minor losses elbow
byMuhammed Fuad Al-Barznji
 
PDF
5 axial flow compressors mod
byMetaabAltaher
 
PDF
Predicting Performance Curves of Centrifugal Pumps in the Absence of OEM Data
byVijay Sarathy
 
PDF
Flash Steam and Steam Condensates in Return Lines
byVijay Sarathy
 
PDF
Governor apparatus | theory of machine Laboratory
bySaif al-din ali
 
PDF
Axial compressor theory - stage-wise isentropic efficiency - 18th March 2010
byCangTo Cheah
 
Evaluation of thermal performance of a typical vapor compression refrigeratio...
bySaif al-din ali
 
Using the convergent steam nozzle type in the entrance
bySaif al-din ali
 
Flow system control
bySaif al-din ali
 
Pipe insulation efficiency study unit |HEAT TRANSFER Laboratory
bySaif al-din ali
 
Flow system control
bySaif al-din ali
 
Fluid Laboratory | Centrifugal fan
bySaif al-din ali
 
Free heat convection |HEAT TRANSFER Laboratory
bySaif al-din ali
 
Induced flow | Fluid Laboratory | U.O.B
bySaif al-din ali
 
forced heat convection | HEAT TRANSFER Laboratory
bySaif al-din ali
 
Aircraft propulsion axial flow compressors off design performance
byAnurak Atthasit
 
Axial compressor theory - stage-by-stage approach - 28th January 2010
byCangTo Cheah
 
Predicting Performance Curves of Centrifugal Pumps in the Absence of OEM Data
byVijay Sarathy
 
Minor losses valve
byMuhammed Fuad Al-Barznji
 
Experimental radial tipped centrifugal fan
byC.Cesar Nascimento
 
Minor losses elbow
byMuhammed Fuad Al-Barznji
 
5 axial flow compressors mod
byMetaabAltaher
 
Predicting Performance Curves of Centrifugal Pumps in the Absence of OEM Data
byVijay Sarathy
 
Flash Steam and Steam Condensates in Return Lines
byVijay Sarathy
 
Governor apparatus | theory of machine Laboratory
bySaif al-din ali
 
Axial compressor theory - stage-wise isentropic efficiency - 18th March 2010
byCangTo Cheah
 

Similar to Nozzles

PPTX
PET 512 NOZZEL.pptx
byokekeekene
 
PPTX
Nozzles - Lecture B
byAhmed Rezk
 
PDF
Nozzles themowasdfghjgasdfgsdfgdfghgfghdsfgh
byssuser25df8b
 
PDF
Ch-1 Nozzles.pdferthjkl;iuytredfghjklyfgdg
byssuser25df8b
 
PDF
report
byJerome David
 
DOC
Unit7 nozzles
byMalaysia
 
PPTX
Nozzles - Lecture A
byAhmed Rezk
 
PPTX
nozzle analysis
byAmmarAlkinani4
 
PPTX
Steam Nozzle
byRohanroy93
 
PDF
Gs2512261235
byIJERA Editor
 
PDF
Gs2512261235
byIJERA Editor
 
PDF
Numerical Investigation of the Perfomance of Convergent Divergent Nozzle
byIJMER
 
PPTX
Compressible flow
byWILLIE TAFADZWA
 
PPT
Compressible flow
byPanneer Selvam
 
PDF
Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of ...
byIJERA Editor
 
PDF
Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of ...
byIJERA Editor
 
PDF
nozzle_diffuser_circulation-2022 (1).pdf
bychandanraj961610
 
PDF
Design & Computational Fluid Dynamics Analyses of an Axisymmetric Nozzle at T...
byIRJET Journal
 
PPT
Flow of Steam through Nozzels
byDinesh Panchal
 
PPT
JP_Choked Flow- fluid mechanics-compressible flow
bysalodoj420
 
PET 512 NOZZEL.pptx
byokekeekene
 
Nozzles - Lecture B
byAhmed Rezk
 
Nozzles themowasdfghjgasdfgsdfgdfghgfghdsfgh
byssuser25df8b
 
Ch-1 Nozzles.pdferthjkl;iuytredfghjklyfgdg
byssuser25df8b
 
report
byJerome David
 
Unit7 nozzles
byMalaysia
 
Nozzles - Lecture A
byAhmed Rezk
 
nozzle analysis
byAmmarAlkinani4
 
Steam Nozzle
byRohanroy93
 
Gs2512261235
byIJERA Editor
 
Gs2512261235
byIJERA Editor
 
Numerical Investigation of the Perfomance of Convergent Divergent Nozzle
byIJMER
 
Compressible flow
byWILLIE TAFADZWA
 
Compressible flow
byPanneer Selvam
 
Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of ...
byIJERA Editor
 
Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of ...
byIJERA Editor
 
nozzle_diffuser_circulation-2022 (1).pdf
bychandanraj961610
 
Design & Computational Fluid Dynamics Analyses of an Axisymmetric Nozzle at T...
byIRJET Journal
 
Flow of Steam through Nozzels
byDinesh Panchal
 
JP_Choked Flow- fluid mechanics-compressible flow
bysalodoj420
 

More from Saif al-din ali

PDF
Nonlinear integral control for dc motor speed control with unknown and variab...
bySaif al-din ali
 
PDF
Design problem
bySaif al-din ali
 
PDF
Power plant steam condenser
bySaif al-din ali
 
PDF
i.c engine
bySaif al-din ali
 
PDF
Control servo motors
bySaif al-din ali
 
PDF
Introduction about i.c engine
bySaif al-din ali
 
PDF
Hybrid car Advanced vehicle technology
bySaif al-din ali
 
PDF
Nonlinear integral control for dc motor speed control
bySaif al-din ali
 
PDF
Weak and strong oblique shock waves2
bySaif al-din ali
 
PDF
Weak and strong oblique shock waves1
bySaif al-din ali
 
PDF
Oblique shock and expansion waves
bySaif al-din ali
 
PDF
Characteristics of shock reflection in the dual solution domain
bySaif al-din ali
 
PDF
Characteristics of shock reflection in the dual solution domain
bySaif al-din ali
 
PDF
Weak and strong oblique shock waves
bySaif al-din ali
 
PDF
The function of management should focus on getting people to work towards and...
bySaif al-din ali
 
PDF
Steam generator-part-1
bySaif al-din ali
 
PDF
Steam generator-part-2
bySaif al-din ali
 
PDF
Me6503 design-of-machine-elements-unit-ii-notes
bySaif al-din ali
 
PDF
Stainless steel
bySaif al-din ali
 
PDF
Superalloys
bySaif al-din ali
 
Nonlinear integral control for dc motor speed control with unknown and variab...
bySaif al-din ali
 
Design problem
bySaif al-din ali
 
Power plant steam condenser
bySaif al-din ali
 
i.c engine
bySaif al-din ali
 
Control servo motors
bySaif al-din ali
 
Introduction about i.c engine
bySaif al-din ali
 
Hybrid car Advanced vehicle technology
bySaif al-din ali
 
Nonlinear integral control for dc motor speed control
bySaif al-din ali
 
Weak and strong oblique shock waves2
bySaif al-din ali
 
Weak and strong oblique shock waves1
bySaif al-din ali
 
Oblique shock and expansion waves
bySaif al-din ali
 
Characteristics of shock reflection in the dual solution domain
bySaif al-din ali
 
Characteristics of shock reflection in the dual solution domain
bySaif al-din ali
 
Weak and strong oblique shock waves
bySaif al-din ali
 
The function of management should focus on getting people to work towards and...
bySaif al-din ali
 
Steam generator-part-1
bySaif al-din ali
 
Steam generator-part-2
bySaif al-din ali
 
Me6503 design-of-machine-elements-unit-ii-notes
bySaif al-din ali
 
Stainless steel
bySaif al-din ali
 
Superalloys
bySaif al-din ali
 

Recently uploaded

PPTX
Using Bangladesh studies in cse why matter ppp.pptx
bymsprinceahmedontor40
 
PDF
Earths-Structure-and-Composition_20260127_110958_0000.pdf
byabdurasabarfaki
 
PDF
Chip Designer's Code - Linux Terminal Part 6 - Text Viewers
byAmr Adel
 
PPTX
Applications of cloud computing in education
byhatimunwala5
 
PPTX
The Half-Life of Preventive Maintenance: Why PM Compliance Fails & How to Res...
byMaintWiz Technologies Private Limited
 
PPTX
M1 - HPE Alletra Storage MP B10000 - presenter.pptx
byThanhBnhNguyn92
 
PPTX
FROM MEASUREMENT TO MEANING : Metrology-Driven Battery Testing for Reliable ...
byRunjhunDutta
 
PDF
God series - Physics video office crossed
byjangidankit8781
 
PDF
Formality - Logic Equivalence Checking - Part 2
byAmr Adel
 
PPTX
Group-3-Ethics - Freedom as foundation for moral acts
byCharlsCasquejo2
 
PDF
PROBLEM SLOVING AND PYTHON PROGRAMMING UNIT 2.pdf
byA R SIVANESH M.E., QIP-PG (Cyber Security)., (Ph.D)
 
PDF
ERTMS-conference-WS8_Presentations_v0.pdf
byEduardo147194
 
PDF
Process Scheduling Scheduling Queue, Types of Sheduler
bySanjay Gunjal
 
PPTX
24ME402-ENGINEERING MATERIALS AND METALLURGY --- UNIT-II
byDJAGADEESH1
 
PDF
(en/zhTW)All_Roads_Lead_to_IPC_DannyJiang
byDanny Jiang
 
PPTX
Tips for Designing Flex Circuits for Medical Applications
byEpec Engineered Technologies
 
PPTX
Filtration-slow sand filtration and rapid sand filtration.pptx
byChemical Engineering Dept. NIT Rourkela-769008, Odisha, India
 
PDF
JVM in the Age of AI: 2026 Edition - Deep Dive
byArtur Skowroński
 
PDF
ME25C05 RE-ENGINEERING FOR INNOVATION LAB.pdf
byVinothkumarM60
 
PDF
Chip Designer's Code - Linux Terminal Part 7.1 - Text Processing
byAmr Adel
 
Using Bangladesh studies in cse why matter ppp.pptx
bymsprinceahmedontor40
 
Earths-Structure-and-Composition_20260127_110958_0000.pdf
byabdurasabarfaki
 
Chip Designer's Code - Linux Terminal Part 6 - Text Viewers
byAmr Adel
 
Applications of cloud computing in education
byhatimunwala5
 
The Half-Life of Preventive Maintenance: Why PM Compliance Fails & How to Res...
byMaintWiz Technologies Private Limited
 
M1 - HPE Alletra Storage MP B10000 - presenter.pptx
byThanhBnhNguyn92
 
FROM MEASUREMENT TO MEANING : Metrology-Driven Battery Testing for Reliable ...
byRunjhunDutta
 
God series - Physics video office crossed
byjangidankit8781
 
Formality - Logic Equivalence Checking - Part 2
byAmr Adel
 
Group-3-Ethics - Freedom as foundation for moral acts
byCharlsCasquejo2
 
PROBLEM SLOVING AND PYTHON PROGRAMMING UNIT 2.pdf
byA R SIVANESH M.E., QIP-PG (Cyber Security)., (Ph.D)
 
ERTMS-conference-WS8_Presentations_v0.pdf
byEduardo147194
 
Process Scheduling Scheduling Queue, Types of Sheduler
bySanjay Gunjal
 
24ME402-ENGINEERING MATERIALS AND METALLURGY --- UNIT-II
byDJAGADEESH1
 
(en/zhTW)All_Roads_Lead_to_IPC_DannyJiang
byDanny Jiang
 
Tips for Designing Flex Circuits for Medical Applications
byEpec Engineered Technologies
 
Filtration-slow sand filtration and rapid sand filtration.pptx
byChemical Engineering Dept. NIT Rourkela-769008, Odisha, India
 
JVM in the Age of AI: 2026 Edition - Deep Dive
byArtur Skowroński
 
ME25C05 RE-ENGINEERING FOR INNOVATION LAB.pdf
byVinothkumarM60
 
Chip Designer's Code - Linux Terminal Part 7.1 - Text Processing
byAmr Adel
 

Nozzles

  • 1.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 1 | P a g e [power plant Laboratory II] University of Baghdad Name: - Saif Al-din Ali -B-
  • 2.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 2 | P a g e TABLE OF CONTENTS Objective............................................................................I INTRODUCTION.............................................................II THEORY.........................................................................III Calculations and results..................................................V DISCUSSION..................................................................VI
  • 3.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 3 | P a g e Experiment Name:- 1. Objective 2. Introduction Two types of nozzles: - 1. Converging-Diverging or " De Laval" Nozzles have been widely used over the last few decades in many engineering contexts, from civil and mechanical to aerospace uses. They are designed to accelerate fluids to supersonic speeds at the nozzle exit. Nearly all rockets make use of this fact to create an effective propulsion system to reach high velocities. Whilst their operation is of a simple appearance, the combination of flows reached, be that subsonic and supersonic and the subsequent change of properties such as pressure, density and temperature make the underlying investigation of their performance more complicated than first expected. Their operation relies on the ratio between the inlet stagnation pressure P0 and outlet back pressure Pb. As this ratio Pb/Po is brought down from unity, the mass flow rate increases till a maximum value is achieved where the Mach number in the throat (see Figure 1) becomes sonic. ( Mach no = 1). This is referred to as "Choked flow". As the ratio is further decreased the flow becomes supersonic in the diverging nozzle, till the design pressure ratio is achieved (0.53 for air) with supersonic flow occurring at the nozzle exit. After this the flow becomes more complicated and normal and oblique shock waves begin to occur inside and outside of the nozzle respectively. The Purpose of this report is to gain an understanding of the nature of this flow by investigating the pressure ratios effects on the mass flow rate of air through the system and the differing pressure distributions that occur at varying lengths into the nozzle. Figure 1. Schematic of a converging-diverging nozzle 2. converging nozzle
  • 4.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 4 | P a g e Converging nozzles, as shown in Figure 2, are tubes with an area that decreases from the nozzle entry to the exit (or throat) of the nozzle. As the nozzle area decreases, the flow velocity increases, with the maximum flow velocity occurring at the nozzle throat. As the inlet flow velocity is increased, flow velocity at the nozzle throat keeps increasing until it reaches Mach 1. At this point, the flow at the throat gets choked, meaning that any further increase of inlet flow velocity will not increase the flow velocity at the throat. It is for this reason that converging nozzles are used to accelerate fluids in the subsonic flow regime alone and can commonly be found on all commercial jets (except for the Concord) as they travel at subsonic speeds. Figure 2. Schematic of a converging nozzle 3. divergent nozzle represents a divergent nozzle for a fluid whose peculiarity is that — decreases with the drop of pressure, i.e., specific volume increases at a faster rate than velocity with the drop of pressure. The area of cross-section should increase as the pressure decreases. Figure 3. diverging nozzle the flow conditions that can be observed in a converging nozzle: 1. No flow condition, where the back-pressure is equal to the total pressure. 2. Subsonic flow, where the flow accelerates as area decreases, and the pressure drops. 3. Subsonic flow, where there is significantly higher acceleration and the pressure drops. 4. Choked flow, where any pressure drop does not accelerate the flow. 5. Choked flow, where the flow expands after the nozzle exit (considered non- isentropic).
  • 5.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 5 | P a g e Figure 4. Flow conditions and regimes in a converging nozzle (theoretical predictions) converging-diverging nozzle shows the following seven profiles in the position versus pressure ratio plot. Note that the first vertical dashed line on the left of the p/pO versus distance along the nozzle plot is the location of the throat, the second vertical dashed line is the location of the nozzle exit, and the horizontal dashed line marks the choked condition. 1. Subsonic flow that never reaches choked condition. 2. Subsonic flow that reaches choked condition but does not attain supersonic velocities (considered isentropic). 3. Subsonic flow that reaches choked condition, with the resulting supersonic flow forming a normal shock, which then experiences subsonic deceleration. Here, the normal shock causes a sudden drop in velocity and an increase in back-pressure, as indicated by the sudden increase in p/pO. 4. Subsonic flow that reaches choked condition, with the resulting supersonic flow forming a normal shock after the nozzle (considered isentropic in the nozzle). 5. Over-expanded flow – the pressure at the nozzle exit is lower than the ambient pressure, causing the jet exiting the nozzle to be highly unstable with huge variations in pressure and velocity as it travels downstream. 6. Flow after the choked condition is supersonic through the nozzle, and no shock is formed. 7. Under-expanded flow – the pressure at the nozzle exit is higher than the ambient pressure and results in similar effects as over-expanded flow. Figure 5. Flow conditions and regimes in a converging-diverging nozzle (theoretical predictions) 3. Theory
  • 6.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 6 | P a g e The characteristic of a nozzle can be graphically represented by diagram which shows the mass flow rate through the nozzle related to the downstream pressure outlet, with fluid conditions maintained constant upstream of the nozzle. In subsonic nozzle conditions the flow rate can be expressed by: 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑨 𝒖 = 𝝅 𝟒 𝑫 𝒕𝒉 𝟐 Where: Po = Total pressures upstream the nozzle, Vo=Specific volume upstream the nozzle Au= the narrow outlet section of the nozzle (throat). P2 = Pressure downstream the nozzle, K = Specific heat ratio (taken l for temperature 170 ° C) For critical pressure downstream the nozzle the mass flow rate will be max (i.e.) the nozzle is chocked can be calculated as: 𝑸 𝒎 𝒂𝒙 = 𝑨 𝒖 𝒑 𝟎 √ 𝒑 𝟎 𝝂 𝟎 ∗ √ 𝟐𝒌 𝒌 − 𝟏 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐
  • 7.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 7 | P a g e 4. Calculations and results 𝑨 𝒖 = 𝝅 𝟒 𝑫 𝒕𝒉 𝟐 = ( 3.14 4 ) ∗ (8 ∗ 10−3)2 = 5.03 ∗ 10−5 𝑚2 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 𝟎. 𝟎𝟑𝟏𝟏𝟐𝟏𝟖 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟗𝟏.𝟐 𝟎.𝟒𝟔𝟒𝟐𝟓 = 𝟎. 𝟎𝟕𝟖𝟔𝟗𝟗 𝒎 𝟑 𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟑. 𝟓 = 1.142857143 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.03950456 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟏.𝟔 𝟎.𝟒𝟔𝟒𝟐𝟓 = 0.090874 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟑 = 1.333333333
  • 8.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 8 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟐. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟐. 𝟓 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.042527341 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟒𝟒.𝟒 𝟎.𝟒𝟔𝟒𝟐𝟓 = 0.099027755 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟐. 𝟓 = 1.6 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎∗𝒗 ∗ √ 𝟐𝒌 𝒌−𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟒 ∗ 𝟏𝟎 𝟓 √𝟒 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟒𝟔𝟒𝟐𝟓𝟏 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟐 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟐 ∗ 𝟏𝟎 𝟓 𝟒 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.041861669 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟓𝟐 𝟎.𝟒𝟔𝟒𝟐𝟓 = 0.101600333 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟒/𝟐 = 2
  • 9.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 9 | P a g e 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟒. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟒. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.035414399 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟏.𝟔 𝟎.𝟑𝟕𝟐𝟗 = 0.101395891 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟒. 𝟓 = 1.11111 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟒 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟒 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.04612388 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟓𝟗.𝟔 𝟎.𝟑𝟕𝟐𝟗 = 0.116163587 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟒 = 1.25
  • 10.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 10 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑. 𝟓 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.051420707 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟖𝟐.𝟒 𝟎.𝟑𝟕𝟐𝟗 = 0.124184098𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟑. 𝟓 = 1.428571429 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟓 ∗ 𝟏𝟎 𝟓 √𝟓 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟕𝟐𝟗 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟑 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟑 ∗ 𝟏𝟎 𝟓 𝟓 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.053222816𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟗𝟕.𝟔 𝟎.𝟑𝟕𝟐𝟗 = 0.129254907 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟓/𝟑 = 1.666666667
  • 11.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 11 | P a g e 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.03500503 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟕𝟓 𝟎.𝟑𝟐𝟏𝟐 = 0.085801054𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟓. 𝟔 = 1.071428571 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟒 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟒 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.041800254 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟗𝟎 𝟎.𝟑𝟐𝟏𝟐 = 0.093990346 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟓. 𝟒 = 1.111111111
  • 12.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 12 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟏 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟏 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.049192115 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟓 𝟎.𝟑𝟐𝟏𝟐 = 0.110768685𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟓. 𝟏 = 1.176470588 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟔 ∗ 𝟏𝟎 𝟓 √𝟔 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟒. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟒. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.052882165𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟒𝟓 𝟎.𝟑𝟐𝟏𝟐 = 0.119301525𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟔/𝟒. 𝟗 = 1.224489796
  • 13.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 13 | P a g e 1. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟔. 𝟓 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟔. 𝟓 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.03500503 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟕𝟓 𝟎.𝟐𝟕𝟓𝟐 = 0.092687731 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟔. 𝟓 = 1.076923077 2. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟔. 𝟐 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟔. 𝟐 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.051562331 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟗𝟎 𝟎.𝟐𝟕𝟓𝟐 = 0.101534322𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟔. 𝟐 = 1.129032258
  • 14.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 14 | P a g e 3. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟗 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.05840326 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟐𝟓 𝟎.𝟐𝟕𝟓𝟐 = 0.119659346 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟓. 𝟗 = 1.186440678 4. 𝑸𝒕𝒉 = 𝑨𝒖 ∗ 𝒑 𝟎 √ 𝒑 𝟎 ∗ 𝒗 ∗ √ 𝟐𝒌 𝒌 − 𝟏 ∗ [( 𝒑 𝐛 𝒑 𝟎 ) 𝟐 𝒌 − ( 𝒑 𝐛 𝒑 𝟎 ) 𝒌+𝟏 𝒌 ] 𝑸𝒕𝒉 = 𝟓. 𝟎𝟑 ∗ 𝟏𝟎−𝟓 ∗ 𝟕 ∗ 𝟏𝟎 𝟓 √𝟕 ∗ 𝟏𝟎 𝟓 ∗ 𝟎. 𝟑𝟐𝟏𝟐 ∗ √ 𝟐 ∗ 𝟏. 𝟏𝟒 𝟏. 𝟏𝟒 − 𝟏 ∗ [( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟐 𝟏.𝟏𝟒 − ( 𝟓. 𝟔 ∗ 𝟏𝟎 𝟓 𝟔 ∗ 𝟏𝟎 𝟓 ) 𝟏.𝟏𝟒+𝟏 𝟏.𝟏𝟒 ] 𝑸𝒕𝒉 = 0.063522547 𝐦 𝟑 /𝒉 𝑸 𝐞𝐱𝐩 = 𝒌√ 𝜟𝒑 𝒗 𝒐 𝑸 𝐞𝐱𝐩 = 𝟓. 𝟔𝟏𝟓√ 𝟏𝟒𝟓 𝟎.𝟐𝟕𝟓𝟐 = 0.12887706 𝒎 𝟑 /𝒉𝒓 𝑹 = 𝑷𝒐/𝑷𝒃 𝑹 = 𝟕 ∗ 𝟓. 𝟔 = 1.25
  • 15.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 15 | P a g e Experimental 1 state Po bar Pb (bar) To ( c) ∆P (mmHg) Tb Vo (m3/kg) 1 3 2.5 145 0.12 137 0.464 2 3 2 145 0.16 130 0.464 3 3 1.5 145 0.19 125 0.464 4 3 1 145 0.2 120 0.464 2 1 4 3.5 150 0.16 144 0.3729 2 4 3 150 0.21 132.5 0.3729 3 4 2.5 150 0.24 132 0.3729 4 4 2 150 0.26 130 0.3729 Theoretical 1 1 5 4.6 165 75 0.3212 2 5 4.4 165 90 0.3212 3 5 4.1 165 125 0.3212 4 5 3.9 165 145 0.3212 2 1 6 5.5 168 75 0.275 2 6 5.2 168 90 0.2752 3 6 4.9 168 125 0.2752 4 6 4.6 168 145 0.2752
  • 16.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 16 | P a g e Experimental Q_exp R Q_th 1 0.078699279 1.142857143 0.031121877 0.0908741 1.333333333 0.039504565 0.099027755 1.6 0.042527341 0.101600333 2 0.041861669 2 0.101395891 1.111111111 0.035414399 0.116163587 1.25 0.04612388 0.124184098 1.428571429 0.051420707 0.129254907 1.666666667 0.053222816 Theoretical 1 0.085801054 1.071428571 0.03500503 0.093990346 1.111111111 0.041800254 0.110768685 1.176470588 0.049192115 0.119301525 1.224489796 0.052882165 2 0.092687731 1.076923077 0.042127888 0.101534322 1.129032258 0.051562331 0.119659346 1.186440678 0.05840326 0.12887706 1.25 0.063522547 Experimental 1 ∆P*760 Pb (bar) +1 Po bar +1 91.2 3.5 4 121.6 3 4 144.4 2.5 4 152 2 4 2 121.6 4.5 5 159.6 4 5 182.4 3.5 5 197.6 3 5 Theoretical 1 75 5.6 6 90 5.4 6 125 5.1 6 145 4.9 6 2 75 6.5 7 90 6.2 7 125 5.9 7 145 5.6 7
  • 17.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 17 | P a g e 5. DISCUSSION 1. 0 0.02 0.04 0.06 0.08 0.1 0.12 0 0.5 1 1.5 2 2.5 Q R Experimental 1 Q_exp Q_th 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0 0.5 1 1.5 2 Q R Experimental 2 Q_exp Q_th
  • 18.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 18 | P a g e In all the drawings, it turns out that the condition is direct and the pitch of the gradient varies depending on the situation 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 1.05 1.1 1.15 1.2 1.25 Q R Theoretical 1 Q_exp Q_th 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 1.05 1.1 1.15 1.2 1.25 1.3 Q R Theoretical 2 Q_exp Q_th
  • 19.
    Saif al-din aliMadi Department of Mechanical Engineering/ College of Engineering/ University of Baghdad 26/11/2018 19 | P a g e What is the effect of the downstream pressure nozzle on the flow rate values? It has great influence on the amount of outflow and the type of flow as per the drawing