This presentation had been prepared for the aircraft propulsion class to my undergraduate and graduate students at Kasetsart University and Chulalongkorn University - Bangkok, Thailand.
SAIF ALDIN ALI MADIN
سيف الدين علي ماضي
S96aif@gmail.com
Presentation
on
Axial Flow Compressor
Introduction
Construction
Working
Design
Main Parts
Stalling
Surging
Stage Losses
Advantages - Disadvantages & Applications
This presentation had been prepared for the aircraft propulsion class to my undergraduate and graduate students at Kasetsart University and Chulalongkorn University - Bangkok, Thailand.
SAIF ALDIN ALI MADIN
سيف الدين علي ماضي
S96aif@gmail.com
Presentation
on
Axial Flow Compressor
Introduction
Construction
Working
Design
Main Parts
Stalling
Surging
Stage Losses
Advantages - Disadvantages & Applications
There are 5 types of jet propulsion engine such as turbojet, turbofan, turboprop, turbo-shaft, and ramjet.Some types of jet propulsive engine are not cover in this slide such as pulse engine and rocket.
There are 5 types of jet propulsion engine such as turbojet, turbofan, turboprop, turbo-shaft, and ramjet.Some types of jet propulsive engine are not cover in this slide such as pulse engine and rocket.
External Air Assisted Shaping of Fuel Spray for Gas Turbine CombustorIDES Editor
In this investigation an attempt has been made to
understand the mechanism for changing fuel spray pattern
by using different geometrical shapes of air flow orifices at
atomizer exit. An airblast atomizer has been specially designed
and constructed for studying fuel spray pattern. The results
of this investigation indicate that an appropriate air orifices
help to obtain desired elliptical fuel spray patterns. This may
enable uniform combustion exit temperature or improved
pattern factor of Gas turbine combustor. Besides this, the
results obtained in this research work may be useful in
multiple applications like development of better spray drying,
spray painting, spray cooling systems and formation of nanoparticles.
ON THE INTEGRATION OF ROTARY HEATER IN GAS FIRED POWER PLANTS WITH POST-COMBUSTION CARBON CAPTURE: A PRELIMINARY EVALUATION - presentation by Laura Herraiz of the University of Edinburgh at the UKCCSRC Natural Gas CCS Network Meeting at GHGT-12, Austin, Texas, October 2014
Hamare Rusoom wa Quyood: Syed Ali Naqi Naqvi Sahab t.s.Jamal Mirza
(Shadi meiN) Yeh rasmeiN jo qaraar pa gai haiN, aksar sahebaane ilm aur ta'leem yaafta afraad jo wasiul khayal honEy ke dawedaar hain woh apni raushan khayali ke muzahere meiN inpar be'zaari karte haiN magar maqaame amal meiN woh bhi inke pa'band nazar aate haiN.Mushkil se koi fard iss se mustasna hogi. Inn par jab eiteraaz kiya jaata hai to woh kahte haiN ke aurtoN se majboor haiN, kuch bas nahin chalta.
Introductory talk on regular expressions for developers who'd like to get their hands dirty. The full tutorial is documented here:
http://tech.bluesmoon.info/2006/04/beginning-regular-expressions.html
Experimental Investigations and Computational Analysis on Subsonic Wind Tunnelijtsrd
This paper disclose the entire approach to design an open circuit subsonic wind tunnel which will be used to consider the wind impact on the airfoil. The current rules and discoveries of the past research works were sought after for plan figuring of different segments of the wind tunnel. Wind speed of 26 m s have been practiced at the test territory. The wind qualities over a symmetrical airfoil are viewed as probably in a low speed wind tunnel. Tests were finished by moving the approach, from 0 to 5 degree. The stream attributes over a symmetrical airfoil are examined tentatively. The pressure distribution on the airfoil area was estimated, lift and drag force were estimated and velocity profiles were acquired. Rishabh Kumar Sahu | Saurabh Sharma | Vivek Swaroop | Vishal Kumar ""Experimental Investigations and Computational Analysis on Subsonic Wind Tunnel"" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-3 | Issue-3 , April 2019, URL: https://www.ijtsrd.com/papers/ijtsrd23511.pdf
Paper URL: https://www.ijtsrd.com/engineering/mechanical-engineering/23511/experimental-investigations-and-computational-analysis-on-subsonic-wind-tunnel/rishabh-kumar-sahu
This presentation had been prepared for the aircraft propulsion class to my undergraduate and graduate students at Kasetsart University and Chulalongkorn University - Bangkok, Thailand.
Numerical Investigation of Single Stage of an Axial Flow Compressor for Effec...IJERA Editor
In present work, a compressor configuration is taken from literature which will be studied for aspect ratio (ratio between length of blade to chord length) influence over performance. Performance in the sense is pressure ratio of compressor. The aspect ratio of the blade is an important parameter and has a strong influence on the performance of axial flow compressor. There are so many literatures available on influence of design parameters of axial flow compressor over its performance. Few literatures only are available for effects of aspect ratio of blade over performance of compressor. A study is proposed to be carried out to verify the effect of aspect ratio on the performance of single stage subsonic compressor through ANSYS-CFX software. The analysis will be carried out for the constant tip diameter of the compressor rotor blade having an aspect ratio 1, 2 and 3 and to obtain the pressure loss and flow parameters of the compressor stage. Further increase in aspect ratio will lead to structural problem of compressor. Therefore, there will be optimum aspect ratio between 2 and 3. Simulation will be conducted to aspect ratios of 2.1, 2.2, 2.3, 2.4, 2.5, 2.6, 2.7, 2.8 and 2.9 to find optimum ratio using ANSYS-CFX commercial CFD software.
This presentation is made to explain the best port locations on various 2D geometries to measure Angle of Attack as a function of Pressure Differential
Technical Support in Thermal Power Generation Sector – Career OpportunitiesAnurak Atthasit
Career opportunities for supporting in thermal power generation business are introduces via this presentation. The presentation had been done for introduction to the undergrad engineering student - Kasetsart University, Thailand.
Combined Cycle Gas Turbine Power Plant Part 1Anurak Atthasit
Introduction to Combined Cycle Gas Turbine Power Plant. Describing the advantage and design limit of the CCGT. Overview of Brayton Cycle and Rankine Cycle - showing some basic thermodynamic to explain some background of CCGT.
High level assessment on Gas Reserves, power demand outlook and the supplies in Thailand and availability shortfall impact with the mitigations foreseen by the government.
A collection came from many sources based on my curiosity - synthesis all of information together with my personal awareness of future crisis. After having heard that China took a major shared of Toulouse Airport - located in the south of France, and many development came across the continents in the same time of economic crisis in Europe and many parts of the world, this is what I curiosly taking my time seeing what was the past performances made by this country. Thanks to many people doing their hard work providing interesting report and articles that I've never forgot to credit to each text and images. Bonne Lecture!
Promenade Culturelle Thailandaise had been carried out in Toulouse in 2003. Ten performers and two painters from Lanna - northern culture of Thailand had performed very special works to french public supported by franco-thai sponsors.
Droplet thermal behavior study with light scattering techniqueAnurak Atthasit
THE 10TH INTERNATIONAL SYMPOSIUM ON FLOW VISUALIZATION
August 26 - 29, 2002, Kyoto, Japan
To present the results obtained from a basic experiment on droplet interaction in a dense linear droplet stream. The interaction of individual droplet with one another and with surrounding influences their transport characteristics.
A vibrating orifice generator produces a stream of monosized droplets. The experiments have been performed by using the electrostatic deviator to obtain the evolution of the main droplet characteristics in a wide range of the spacing parameter value Co (ratio between droplet spacing to droplet diameter). The basic experiment allows quantifying precisely the evolution of the drag coefficient and the droplet evaporation rate for different droplet spacings.
Overview of the fundamental roles in Hydropower generation and the components involved in wider Electrical Engineering.
This paper presents the design and construction of hydroelectric dams from the hydrologist’s survey of the valley before construction, all aspects and involved disciplines, fluid dynamics, structural engineering, generation and mains frequency regulation to the very transmission of power through the network in the United Kingdom.
Author: Robbie Edward Sayers
Collaborators and co editors: Charlie Sims and Connor Healey.
(C) 2024 Robbie E. Sayers
Saudi Arabia stands as a titan in the global energy landscape, renowned for its abundant oil and gas resources. It's the largest exporter of petroleum and holds some of the world's most significant reserves. Let's delve into the top 10 oil and gas projects shaping Saudi Arabia's energy future in 2024.
Hybrid optimization of pumped hydro system and solar- Engr. Abdul-Azeez.pdffxintegritypublishin
Advancements in technology unveil a myriad of electrical and electronic breakthroughs geared towards efficiently harnessing limited resources to meet human energy demands. The optimization of hybrid solar PV panels and pumped hydro energy supply systems plays a pivotal role in utilizing natural resources effectively. This initiative not only benefits humanity but also fosters environmental sustainability. The study investigated the design optimization of these hybrid systems, focusing on understanding solar radiation patterns, identifying geographical influences on solar radiation, formulating a mathematical model for system optimization, and determining the optimal configuration of PV panels and pumped hydro storage. Through a comparative analysis approach and eight weeks of data collection, the study addressed key research questions related to solar radiation patterns and optimal system design. The findings highlighted regions with heightened solar radiation levels, showcasing substantial potential for power generation and emphasizing the system's efficiency. Optimizing system design significantly boosted power generation, promoted renewable energy utilization, and enhanced energy storage capacity. The study underscored the benefits of optimizing hybrid solar PV panels and pumped hydro energy supply systems for sustainable energy usage. Optimizing the design of solar PV panels and pumped hydro energy supply systems as examined across diverse climatic conditions in a developing country, not only enhances power generation but also improves the integration of renewable energy sources and boosts energy storage capacities, particularly beneficial for less economically prosperous regions. Additionally, the study provides valuable insights for advancing energy research in economically viable areas. Recommendations included conducting site-specific assessments, utilizing advanced modeling tools, implementing regular maintenance protocols, and enhancing communication among system components.
Immunizing Image Classifiers Against Localized Adversary Attacksgerogepatton
This paper addresses the vulnerability of deep learning models, particularly convolutional neural networks
(CNN)s, to adversarial attacks and presents a proactive training technique designed to counter them. We
introduce a novel volumization algorithm, which transforms 2D images into 3D volumetric representations.
When combined with 3D convolution and deep curriculum learning optimization (CLO), itsignificantly improves
the immunity of models against localized universal attacks by up to 40%. We evaluate our proposed approach
using contemporary CNN architectures and the modified Canadian Institute for Advanced Research (CIFAR-10
and CIFAR-100) and ImageNet Large Scale Visual Recognition Challenge (ILSVRC12) datasets, showcasing
accuracy improvements over previous techniques. The results indicate that the combination of the volumetric
input and curriculum learning holds significant promise for mitigating adversarial attacks without necessitating
adversary training.
Cosmetic shop management system project report.pdfKamal Acharya
Buying new cosmetic products is difficult. It can even be scary for those who have sensitive skin and are prone to skin trouble. The information needed to alleviate this problem is on the back of each product, but it's thought to interpret those ingredient lists unless you have a background in chemistry.
Instead of buying and hoping for the best, we can use data science to help us predict which products may be good fits for us. It includes various function programs to do the above mentioned tasks.
Data file handling has been effectively used in the program.
The automated cosmetic shop management system should deal with the automation of general workflow and administration process of the shop. The main processes of the system focus on customer's request where the system is able to search the most appropriate products and deliver it to the customers. It should help the employees to quickly identify the list of cosmetic product that have reached the minimum quantity and also keep a track of expired date for each cosmetic product. It should help the employees to find the rack number in which the product is placed.It is also Faster and more efficient way.
NO1 Uk best vashikaran specialist in delhi vashikaran baba near me online vas...Amil Baba Dawood bangali
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RAT: Retrieval Augmented Thoughts Elicit Context-Aware Reasoning in Long-Hori...
Aircraft propulsion combustor diffusor
1. Aeropropulsion
Unit
Combustor and Diffuser Design
2005 - 2010
International School of Engineering, Chulalongkorn University
Regular Program and International Double Degree Program, Kasetsart University
Assist. Prof. Anurak Atthasit, Ph.D.
2. Aeropropulsion
Unit
2
A. ATTHASIT
Kasetsart University
Topics
1.Combustion chamber design approach
2.Pressure loss in combustion chamber
3.Combustion chamber description
4.Combustor’s diffuser
5.Performance criteria
3. Aeropropulsion
Unit
3
A. ATTHASIT
Kasetsart University
Combustion Chamber : Problem
Compressor outlet velocity 170 m/s
Combustion chamber :
1.High velocity : impractical to attempt to burn fuel in air flowing at such high velocities
2.High velocity : high loss due to high friction
High inflow : impractical to attempt to burn fuel in air flowing at such high velocity
4. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 5
Pressure Drop in Burner
burner cold hot P P P
Combustor design requirements:
Minimizing the pressure drops
5. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 6
Pressure Drop in Burner
Cold loss: sum of the losses arising in
the diffuser and the liner
burner ,cold 2
max
P
k M
P 2
Hot loss: occurs whenever heat is added
to a flowing gas
2 4
burner ,hot
3
T
P 0.5 U 1
T
Ref: Roffe, Gerald and Venkataramani (1978)
6. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 7
Pressure Loss – Cold Loss
burner ,cold 2
max
P
k M
P 2
Ref: Roffe, Gerald and Venkataramani (1978)
Cold loss: the total pressure loss which results from sudden
expansions and contractions in flow are
k resistance coefficient (function of the system geometry)
γ specific heat ratio
Mmax the highest Mach number achieved in the contraction based on
the area ratio and mass flow
7. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 8
Pressure Loss – Cold Loss
ref
max
M
M
1 B / 1000
Mref the reference Mach number
B the flameholder blockage (50-80%)
the ratio of the total blockage area
at the station where the base of the
flameholder is located to the
reference area of the combustor
8. Aeropropulsion
Unit
9
A. ATTHASIT
Kasetsart University
Combustion Chamber – Design Limitation
Flame front
Air-fuel ratio 18:1 – 24:1
Low efficiency
9. Aeropropulsion
Unit
10
A. ATTHASIT
Kasetsart University
Combustion Chamber : Solutions
?
- Burn it slowly - Increasing the reaction surface
10. Aeropropulsion
Unit
11
A. ATTHASIT
Kasetsart University
Combustion chamber - Anatomy
Vair inlet 170 m/s
Diffuser :
reduce 5 time
air speed
Recirculation zone : Primary zone: air-fuel ratio 18-24
Diluted zone:
burned product + fresh air
11. Aeropropulsion
Unit
13
A. ATTHASIT
Kasetsart University
Dilute Zone
Dilute zone:
Fresh air is mixing with the hot burned products to reduce their temperature to a value that is acceptable to the turbine
12. Aeropropulsion
Unit
14
A. ATTHASIT
Kasetsart University
Diffuser
The function of the diffuser is not only to reduce the velocity of the combustor inlet air, but also to recover a much of the dynamic pressure as possible, and to present the liner with a smooth and stable flow
13. Aeropropulsion
Unit
15
A. ATTHASIT
Kasetsart University
Diffuser – 2 types
Flare (or step) Diffuser
Dump Diffuser
14. Aeropropulsion
Unit
16
A. ATTHASIT
Kasetsart University
Influence of divergence angle on pressure loss
Divergence angle
Loss
Stall loss
Friction loss
Short diffuser:
High divergence angle
Stall losses arising from boundary layer separation
Long diffuser:
Low divergence angle
Pressure loss is high due to skin friction along the walls
Optimum: 6-12 deg.
15. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 17
Diffuser Geometry
W
N
θ
L
1
L
AR 1 2 sin
W
R N
L
θ
2
1 1
L L
AR 1 2 sin sin
R R
Two-dimensional type
Conical-type
16. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 18
Diffuser Geometry
W
N
θ
L
R N
L
θ
AR Area ratio, the primary function of the
diffuser achieving a prescribed
reduction in velocity
L/W or L/R non dimensional length, defines the
overall pressure gradient (the principal
factor in boundary layer development)
2θ the divergence angle
17. Aeropropulsion
Unit
19
A. ATTHASIT
Kasetsart University
Flow Regime in the Diffuser
1.No stall
2.Transitory stall: the eddies are formed + pulsating flow between core and boundary layer
3.Fully developed stall: the major portion of the diffuser is filled with a large triangular shaped recirculation region
4.Jet flow (occurs only at high angles of divergence)
18. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 20
Performance Criteria
Obj: to understand the efficiency
parameters related to the diffuser
Mean velocity
m
u
A
Dynamic pressure
2 u
q
2
Pressure loss :
(internal energy loss
+ redistribution of velocity between
inlet and outlet)
diff t1 t2 P P P
Area Ratio (AR) :
2 1 1
1 2 2
A u u
AR
A u u
19. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 21
Static Pressure Rise in Diffuser
Several useful parameters for
expressing diffuser performance can
be derived from this equation
1 1 2 2 diff
2 1 1 2 diff
p q p q P
1
p p q 1 P
AR
Bernoulli:
20. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 22
Pressure-Recovery Coefficient
2 1
p
p p
C
q
Specific case: No losses (ideal pressure-recovery coefficient)
2 1 1 2 diff
1
p p q 1 P
AR
No pressure loss
2 1ideal
p 2
1
p p 1
C 1
q AR
(Dependent solely on area ratio)
21. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 23
Overall Efficiency
p,measured
p,ideal
C
C
0.5 0.9
Overall efficiency varies depending on the geometry
and flow conditions
22. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 24
Loss Coefficient
t1 t 2
1
P P
q
Where
t 2
t 2
2
P
P
m
Constant mass flow
t1 t 2
1
P P
q
-Flare diffusers λ~0.15
-Dump diffusers λ~0.45
23. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 25
Kinetic Energy Coefficient
With non uniform flows the kinetic energy flux is greater than it
would be for the same flow rate under uniform flow conditions
2
2
1
u udA
2
1
u m
2
α=1 completely uniform flow
α=2 flow on the point of separation
24. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 26
Kinetic Energy Coefficient
Recall: under uniform flow condition α=1 completely uniform flow
1 1 2 2 diff p q p q P
non uniform flow condition α≠1
1 1 1 2 2 2 diff p q p q P
25. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 27
Diffuser Performance
Parameters: Ch13P01
2
p,ideal 2
1
2 1
p
1 1
2 1
2
1 1 2
p,ideal p
1
C 1
AR
p p
C
q
p p
q
AR
C C
Proof these expressions :
Prove
• Obj: Able to
use the
fundamental
equation
under the
correct
assumptions
Analysis
• Obj:
Understand
the physical
meaning of
each
parameters
Calculation
• Obj: Able to
solve the
relations
under the
constraints of
corrected unit,
constant, …
etc.
26. Aeropropulsion
Unit
28
A. ATTHASIT
Kasetsart University
Prediction of the Diffuser Performance
Range of validity
-The flow is subsonic, but not necessary incompressible
-The inlet Reynolds number is greater than 2.5x104, so that problems of transition from laminar to turbulent flow are avoided
-The inlet velocity profile is symmetric
- Flow within the diffuser is essentially unstalled
- The diffuser itself is symmetrical and non turning
27. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 29
Prediction of the Diffuser
Performance : Conical Diffuser
R N
L
θ
Performance chart for conical diffusers B1=0.02
(adapted from Sovran and Klomp 1967)
Maximum pressure recovery for
non-dimensional length at given
area ratio
The diffuser non-dimensional
length, producing the maximum
pressure recovery at a prescribed
area ratio
28. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 30
Performance Prediction: two-dimensional
diffusers
W
N
θ
L
Overall effectiveness
Effectiveness is diminished by an
increase in inlet boundary layer
thickness
Small effect of boundary layer on
pressure recovery
Reneau et al (1967)
Domain of validation:
5<2θ<30 deg.
N/W1 : 1.5-25
29. Aeropropulsion
Unit
31
A. ATTHASIT
Kasetsart University
Design a conical diffuser to give maximum pressure recovery under a non- dimensional length N/R1 = 4.66 using the data given by Sovran and Klomp 1967
Diffuser Preliminary Design: Ch13P02
Prove
•Obj: Able to use the fundamental equation under the correct assumptions
Analysis
•Obj: Understand the physical meaning of each parameters
Calculation
•Obj: Able to solve the relations under the constraints of corrected unit, constant, … etc.
30. Aeropropulsion
Unit
32
A. ATTHASIT
Kasetsart University
From the graph, using log-linear scaling, the appropriate value of Cp is 0.6 and the corresponding value of AR is 2.13.
Cpi = 1-(1/2. 132) = 0.78.
Hence, η = 0.6/0.78 = 0.77. Transposing the expression given in the given figure, the included cone angle can be found: 2θ = 2tan-1{(AR0.5 - l)/(L/Rl)} = 11.26deg.
Diffuser Preliminary Design: Ch13P02 - Solution
31. Aeropropulsion
Unit
33
A. ATTHASIT
Kasetsart University
Diffuser Preliminary Design: Ch13P03
Design a conical diffuser to give maximum pressure recovery at a prescribed area ratio AR = 1.8
Prove
•Obj: Able to use the fundamental equation under the correct assumptions
Analysis
•Obj: Understand the physical meaning of each parameters
Calculation
•Obj: Able to solve the relations under the constraints of corrected unit, constant, … etc.
32. Aeropropulsion
Unit
34
A. ATTHASIT
Kasetsart University
Diffuser Preliminary Design: Ch13P02 - Solution
From the graph, Cp = 0.6 and N/R1 = 7.85 (using log-linear scaling). Thus, 2θ = 2tan-1{(AR0.5 - l)/(L/Rl)} 2θ = 2tar1-1{(1.80.5 - 1)/7.85) = 5deg. Cpi = 1 - (1/1.82 ) = 0.69 and η= 0.6/0.69 = 0.87
Do not forget showing an interpolation procedure
33. Aeropropulsion
Unit
35
A. ATTHASIT
Kasetsart University
Diffuser Preliminary Design: Ch13P03
An annular diffuser with an area ratio, AR = 2.0 is tested at low speed and the results obtained give the following data:
at entry, α1 = 1.059, B1 = 0.109
at exit, α 2 = 1.543, B2 = 0.364, Cp = 0.577
Determine the diffuser efficiency.
NB B1 and B2 are the fractions of the area blocked by the wall boundary layers
at inlet and exit (displacement thicknesses) and are included only to illustrate the
profound effect the diffusion process has on boundary layer thickening
Prove
•Obj: Able to use the fundamental equation under the correct assumptions
Analysis
•Obj: Understand the physical meaning of each parameters
Calculation
•Obj: Able to solve the relations under the constraints of corrected unit, constant, … etc.
34. Aeropropulsion
Unit
Kasetsart University A. ATTHASIT 36
Conclusion
*
2
1
*
2
1
1
*
*
2
*
1
2( 1)
2
*
1
2
1
1
2
1
2
1
1
2
1
2
1
1
2
1
1
1 2
1
2
T
T
M
P
P
M
P
P
T
M
T
P
m AV AM
R T
M
A
A M
2
0
0 t
dA d du
A u
udu dP
dh dh udu
dP d dT
P T
a
P
P dP
T dT
d
A dA
u du
P
T
A
u
dx
2
dP
P
See You
Next Class!