This document provides an overview of rocket-based combined cycle (RBCC) engines. It discusses how RBCC engines can operate in different modes, including ejector, ramjet, scramjet, and rocket modes, depending on flight speed. The document describes the components of RBCC engines, including the inlet, combustor, and nozzle. It explains the ideal thermodynamic cycle of RBCC engines in ejector mode and highlights features such as higher specific impulse compared to rockets and lower onboard oxidizer requirements compared to air-breathing engines. The document also notes challenges in developing RBCC engines and their potential to enable single-stage-to-orbit vehicles.
RAMJET is a type of jet engine in which the air drawn in for combustion is compressed solely by the forward motion of the aircraft.
A ramjet uses this high pressure in front of the engine to force air through the tube, where it is heated by combusting some of it with fuel.
It is then passed through a nozzle to accelerate it to supersonic speeds. This acceleration gives the ramjet forward thrust.
Mini project ppt on working of steam turbine and its auxiliariesjyotishmathi college
A steam turbine is a mechanical device that extracts thermal energy from pressurized steam, and converts it into rotary motion. Its modern manifestation was invented by Sir Charles Parsons in 1884.
RAMJET is a type of jet engine in which the air drawn in for combustion is compressed solely by the forward motion of the aircraft.
A ramjet uses this high pressure in front of the engine to force air through the tube, where it is heated by combusting some of it with fuel.
It is then passed through a nozzle to accelerate it to supersonic speeds. This acceleration gives the ramjet forward thrust.
Mini project ppt on working of steam turbine and its auxiliariesjyotishmathi college
A steam turbine is a mechanical device that extracts thermal energy from pressurized steam, and converts it into rotary motion. Its modern manifestation was invented by Sir Charles Parsons in 1884.
Gas turbine engines derive their power from burning fuel in a combustion chamber and using the fast flowing combustion gases to drive a turbine in much the same way as the high pressure steam drives a steam turbine.
The gas turbine is the engine at the heart of the power plant that produces electric current. A gas turbine is a combustion engine that can convert natural gas or other liquid fuels to mechanical energy. This energy then drives a generator that produces electrical energy.
In a gas turbine, gas is ignited under pressure and combustible high-pressure, high-temperature gases are produced. The combustible gases power a turbine, which in turn powers a generator. In a boiler power plant, electricity is generated by heating water to produce steam which, via a turbine, powers a generator.
Here are the presentations from our Meet the Engineer event on 10th June 2015, supported by the Automotive Council and the UK's Advanced Propulsion Centre.
The event included 21 'pecha kucha' style technology pitches from SME Technology Developers representing a range of early stage through to production ready Automotive innovations.
Brayton or Joule cycle -P-V diagram and thermal efficiency. Construction and working of gas turbine i] Open cycle ii] Closed cycle gas turbine, simple circuit, Comparison, P-V & T-S diagramTurbojet and Turboprop Engine and Application
this will help to understand the basic knowledge of diesel power plant .
For generating electrical power, it is essential to rotate the rotor of an alternator by means of a prime mover. The prime mover can be driven by different methods. Using diesel engine as prime mover is one of the popular methods of generating power. When prime mover of the alternators is diesel engine, the power station is called diesel power station.The mechanical power required for driving alternator comes from combustion of diesel. As the diesel costs high, this type of power station is not suitable for producing power in large scale in our country. But for small scale production of electric power, and where, there is no other easily available alternatives of producing electric power, diesel power station are used. Steam power stations and hydro power plants are mainly used to produce maximum portion of the electrical load demands. But for steam power station, sufficient supply of coal and water are required.
Advantages of Diesel Power Station:-
This is simple in design point of view.
Required very small space.
It can also be designed for portable use.
It has quick starting facility, the small diesel generator set can be started within few seconds.
It can also be stopped as when required stopping small size diesel power station, even easier than it’s starting
As these machines can easily be started and stopped as when required, there may not be any standby loss in the system.
Cooling is easy and required smaller quantity of water in this type power station.
Initial cost is less than other types of power station.
Thermal efficiency of diesel is quite higher than of coal.
Disadvantages of Diesel Power Station:-
As we have already mentioned, the cost of diesel is very high compared to coal. This is the main reason for which a diesel power plant is not getting popularity over other means of generating power. In other words the running cost of this plant is higher compared to steam and hydro power plants.
The plant generally used to produce small power requirement.
Cost of lubricants is high.
Maintenance is quite complex and costs high.
Plant does not work satisfactorily under overload conditions for a longer period
Here are the presentations from Productiv's 4th Meet the Engineer event, supported by the Automotive Council and the UK's Advanced Propulsion Centre.
The event included 21 'pecha kucha' style technology pitches from SME Technology Developers representing a range of early stage through to production ready Automotive innovations.
The event was host to an audience of OEMs and Tier 1s, including Jaguar Land Rover, Ford, Tevva Motors, Alexander Dennis, Optare, Caterpillar, Schaefller and many more.
Thank you to all the Technology Developers for delivering high quality and engaging pitches. Thank you to the audience for listening and engaging with the presenters in the networking and exhibition sessions.
If you'd like to learn more about the event, connect with one of the speakers, or talk about your technology industrialisation and proving production challenges then please get in touch with us.
The Proving Factory, Gielgud Way, Coventry CV2 2SA
enquiries@productivgroup.co.uk | +442476 309 291
www.productivgroup.co.uk
conceptual design is a bridge between what is in our mind and what could be in market,the hybrid motor uses propellants in different physical phases and which is more advantageous than solid propellant engines.
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B.tech Mechanical Seminar - RBCC Engines
1. Overview of Rocket Based
Combined Cycle Engines
(RBCC Engines)
AKSHAY REJI
1
2. Introduction
Rockets
Carry their on oxidizer.
• Characterized by high engine
thrust to weight ratio ( 70 -
100) and relatively low
trajectory average specific
impulse ( 350 – 450 sec for
LH2/LOX systems).
Air breathing engines
• Don’t carry a substantial
amount of onboard oxidizer.
• Higher specific impulse ( 1500 –
500 sec for LH2).
• Low thrust to weight ratio
around 5 – 15.
2
Jet engines can be classified into air breathing and non air breathing
engines ( rocket engines ).
3. Terms and Definitions
• Specific Impulse : Total impulse delivered per unit
of propellant consumed and is dimensionally equivalent to the
generated thrust divided by the propellant mass flow rate or weight
flow rate.
• Thrust to weight ratio : Dimensionless ratio of thrust to weight of
a jet engine, or a vehicle propelled by such an engine that indicates
the performance of the engine or vehicle.
• Mach Number (M) : ratio of the velocity of a fluid to the velocity of
sound in that fluid.
Subsonic : M < 1 Transonic : M = 1
Supersonic : 1 < M < 5 Hypersonic : M > 5
3
4. Rocket Based Combined Cycle (RBCC) Engines - 1
Defined as a combined cycle engine whose primary propulsion element
is the chemical rocket.
• Also known as air – augmented rocket or air breathing rocket engines.
• The rocket and ramjet share the same flow path, thus leaving out
complex structures and reducing redundant weight.
• Offers thrust to weight ratios of 25 – 40 and specific impulse that are
higher than rockets (420 – 800 sec)
• Completely integrated flow path used throughout the entire ballistic
trajectory so
that it can take full advantage of various thermodynamic cycles.
4
5. Rocket Based Combined Cycle (RBCC) Engines - 2
• The high-temperature and fuel-
rich gas ejected from the rocket
nozzle is called the primary flow
and the entrained air is called
the secondary flow.
• The ability to utilize the rocket as
an ejector increases the engine
mass flow, therefore, thrust.
5
Fig 1. Layout of a RBCC Engine
Zeyu Dong, Survey on key techniques of rocket-based combined-
cycle engine in ejector mode.
6. Need of an RBCC Engine
• Engines with a single mode cannot work effectively in the full
speed range.
• Rocket engines are currently the only engines with the
ability to launch an aircraft into orbit.
• Additional propulsion system is needed to implement orbit
change and the re-entry mission.
6
7. Working process of a typical RBCC engine – Part 1
Ejector Mode
• Before the period of Mach 2.
• The eject rocket is ignited and
the fuel-rich plume mixes and
reacts with the secondary flow
in the main combustor.
• The rocket acts as an ejector to
pump
the airflow into the engine.
Ramjet Mode
• Between Mach 2 and Mach 5.
• The free flow is compressed and
slowed down after a normal shock
wave in the inlet, before mixing
and reacting with the fuel in the
combustor.
• The eject rocket is shut down, but
can also supply fuel to the
combustor.
7
8. Working process of a typical RBCC engine – Part 1
Scramjet Mode
• Speed exceeds Mach 5.
• The free flow’s total enthalpy
is too high to maintain an
effective reaction in subsonic
conditions.
• inlet and isolator may still slow
down the free flow by
generating a series of shock
waves.
Rocket Mode
• When the inlet fails to capture
enough airflow to maintain
combustion, the eject rocket is
re-ignited and the inlet is closed.
• The rocket provides all the
thrust in this mode and no
secondary flow passes into the
flow path.
8
9. Operational Modes
• Fig. 2 Operational modes of an RBCC engine
Zeyu Dong, Survey on key techniques of rocket-based combined-
cycle engine in ejector mode.
9
10. Components of RBCC engines - 1
• Inlet / Fore body
Capture freestream air and prepare it for the combustor section while
producing minimum drag losses.
The goals of inlet design are to produce uniform flow at the combustor
entrance, no boundary layer separation, low drag, low heat transfer
and a minimal total pressure losses
Act as the primary compressor of the ambient air.
10
11. Components of RBCC engines -2
Combuster
• Heart of the combined cycle design.
• Integrates the various propulsion modes into a single propulsion unit.
• The rocket ejector is the primary feature of the combustor section
operating in three of the four propulsion modes: as the ejector in air
augmented rocket mode; as a fuel injector in scramjet mode; and
alone in all-rocket mode for orbital insertion.
11
12. Components of RBCC engines -3
• Nozzle
• Optimally expand the products of combustion in order to maximize
potential thrust.
• The nozzle must be integrated with the preceding engine section and
the following section – afterbody.
• Excessive drag at transonic and supersonic speed due to large
expansion ration nozzle can be reduced through the use of external
hydrogen burning.
• The nozzle is the thrust producer of the engine and its exhaust system
has potentially strong influence on vehicle stability and control.
12
13. Basic operating principle of the RBCC ejector mode
• Used from takeoff through to the low supersonic flight regime.
• Rocket acts as an ejector to pump the airflow into the engine.
• Under the effects of viscous interaction, the low-velocity secondary
flow is ingested into the high-velocity primary flow in the mixing duct.
• Exhaust is discharged into the atmosphere through the RBCC nozzle.
13
14. Ideal thermodynamic cycle of ejector mode
• Black line and the red line represent the
thermodynamic process of primary flow
and secondary flow.
• Propellant is pressurized by the fuel
supply system
• Combustion process in the primary rocket
chamber.
• Burned gas at high temperature and
pressure carries out an isentropic
expansion in the rocket nozzle.
14
Fig 3. Ideal cycle of a RBCC engine in ejector mode
Zeyu Dong, Survey on key techniques of rocket-based combined-cycle
engine in ejector mode.
15. Features of RBCC compared to other combined cycle engines - 1
• Afterburning in rocket-ejector mode, using the ramjet/scramjet fuel
injectors, increases the thrust and specific impulse.
• Ratio of the bypass air to the rocket exhaust mass the specific
impulse continues to increase as the cycle more
closely resembles ramjet operation.
• In ramjet and scramjet modes, the rocket could be advantageously
used as a fuel injector and mixing enhancer.
• In the rocket-only mode, the use of the engine duct as a highly
expanded nozzle at high altitudes increases the specific impulse of
that mode of operation.
• Reduction in the amount of onboard oxidizer required.
15
16. Features of RBCC compared to other combined cycle engines - 2
• Vehicle propellant mass fractions for RBCC-powered vehicles are projected
to be around 70%, as compared to 90% for all-rocket vehicles ( propellant
mass fraction - portion of a vehicle's mass which does not reach the
destination).
• In the rocket-ejector mode, RBCC systems can provide vehicle thrust-to-
weight ratios greater
than one and are therefore capable of vertical takeoff and landing.
• The cryogenic fuel can be used in airbreathing modes as a heat sink to
increase the density of the inlet airflow, thus increasing the work output.
16
17. Challenges
• Braod range of chemical constituents produced as a result of
combustion.
• Difference in the operation condition of various modes.
• Cooling techniques and active cooling must be defined.
• Realizing smooth transition among working modes.
• Propulsion/ airframe integration design, and thermal protection
design.
17
18. Summary
• RBCC engine
• Working modes
• Different components
• Ejector mode of a RBCC Engine
• Features
18
19. Conclusion
• Combined cycle engines are the future of reusable launch vehicles
and RBCC engines development is a necessity to create SSTO vehicles.
• Due to technical limitations it not easy to generate a practical RBCC
engine powered aircraft. However, research on RBCC engine
techniques will greatly benefit the
related disciplines and the payoff for future space round trips.
19
20. References
1. ZHANG, Zhen-guo WANG, Wei HUANG, Jian CHEN, Ming-bo SUN - The
overall layout of rocket-based combined-cycle engines: a review, 2019
2. Zeyu Donga, Mingbo Suna, Zhenguo Wanga, Jian Chenb, Zun Caia -
Survey on key techniques of rocket-based combined-cycle engine in
ejector mode , 2017
3. Kent T. Chojnacki and Clark W. Hawk - An Assessment of LlleRocket-Basec
Combined Cycle Propulsion System for Earth-to-Orbit Transportation
20