Aircraft Propulsion and Gas Turbine Engines

El-Sayed, Ahmed F.

doi:10.1201/9781420008777

Cited by 122 publications

(160 citation statements)

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“…(3.1) for a single stream aero engine (ramjet or turbojet engine), the thrust force depends on the inlet and outlet air mass flow rates, fuel-to-air ratio, flight speed, exhaust speed, and exhaust and ambient pressures [1]. Though it looked like a simple task to identify the factors listed above, each of them is dependent on several parameters.…”

Section: Factors Affecting Thrustmentioning

confidence: 98%

Performance Parameters of Jet Engines

El-Sayed

2016

Fundamentals of Aircraft and Rocket Propulsion

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The designer of an aircraft engine must recognize the differing requirements for take-off, climb, cruise, and maneuvering. The relative importance of these being different for civil and military applications and for long-and short-haul aircrafts. In the early aircrafts, it was common practice to focus on the take-off thrust. This is no longer adequate for later and present day aircrafts. For long-range civil transports like Boeing 747, 777, 787 and Airbus A 340, A380 (the world's truly double-deck airliner), A350 XWB (extra wide body), the fuel consumption through some 10 or more flight hours is the dominant parameter. Military aircrafts have numerous criteria like the rate of climb, maneuverability for fighters, short take-off distance for aircrafts operating from air carriers, maximum ceilings for high altitude reconnaissance aircrafts like SR-71 Blackbird aircrafts. For civil and military freighter airplanes, the maximum payload is its main requirement.In all types of aircrafts, the engines are requested to provide efficiently the thrust force necessary for their propelling during different flight phases and at different operating conditions including hottest/coldest ambient temperature and rainy/ windy/snowing weather.This chapter resembles a first window for air breathing engines. It starts by a derivation for the thrust force or the propelling force generated in the direction opposite to the flow of air entering the engine in accordance with Newton's laws of motion. Consequently, all jet engines including rocket motors belong to the class of power plants called reaction engines. It is the internal imbalance of forces within the gas turbine engines that give all reaction engines their names. The propulsive force developed by a jet engine is the result of a complex series of actions and reactions that occur within the engine. The thrust constituents and the different factors affecting the thrust are next explained. Some of these factors are related to the engine, others are related to the medium in which the engine operates.

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Section: Factors Affecting Thrustmentioning

confidence: 98%

Performance Parameters of Jet Engines

El-Sayed

2016

Fundamentals of Aircraft and Rocket Propulsion

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“…The flow characteristics in podded intakes for four flow conditions are illustrated in Figure 8. In ground running (Figure 8-a), there will [ 10] be no effective free stream velocity that results in a large induced flow capture area causing the streamlines to converge into the intake area. The ratio between the upstream capture area to the inletarea approaches infinity.…”

Section: Flow Characteristics In Intakementioning

confidence: 99%

Aero-Engines Intake: A Review and Case Study

El-Sayed¹

2016

J Robot Mech Eng Resr

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This paper presents an aerodynamic review for intakes of aero-engines. Classification of different types is introduced for both subsonic and supersonic aircrafts. Important parameters influencing intake performance like pressure recovery and spillage drag are discussed. In addition, crucial performance issues such as the angle of attack, ground vortex, swirl flow, noise propagation and icing are presented. These are critical issues which are carefully considered by airframe rather than engine manufacturers. Intake icing may be extremely dangerous and leads to drastic decrease in air mass flow and consequently aircraft propulsion.Calculation of intake performance is explained. The effect of intake performance on the whole engine performance is highlighted. Numerical analyses for present and previous researches are explained and critical parameters are identified.Finally, a case study resembling the intake of a high bypass ratio turbofan engine (in close similarity to that of GE CF-6 Turbofan Engine) is numerically analysed using the commercial code "ESI-CFD 2010" is thoroughly described and analysed. This paper is the first of a series of research work that will cover several R & D activities in HBPR and future EBPR turbofan intakes.

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“…The pressure at the end of combustion depends on the pressure drop in the combustion process itself. It may be expressed as [15]:…”

Section: Combustion Chamber (Cc)mentioning

confidence: 99%

Power System Analysis of an Aero-Engine

Turan¹,

Aydın²

2015

JPEE

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The aim of this study is analyzed in detail for better understanding of energy and power of an aero-engine. In this regard, this study presents energy equations were applied to the turbofan engine components. The engine has a thrust range of 82 to 109 kN. It consists of fan, axial low pressure compressor (LPC), axial high pressure compressor (HPC), an annular combustion chamber, high-pressure turbine (HPT) and low pressure turbine (LPT). The results show that power of the engine flow approaches a maximum value to be 82.85 MW in the combustor outlet, while minimum power is observed at LPC inlet with the value of 1.37 MW. Furthermore, important parameters of the engine are also analyzed from reverse-engineering method. It is expected that results of this study will be beneficial of power, cogeneration and aero-propulsive generation systems in similar environment.

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Aircraft Propulsion and Gas Turbine Engines

Cited by 122 publications

References 0 publications

Performance Parameters of Jet Engines

Performance Parameters of Jet Engines

Aero-Engines Intake: A Review and Case Study

Power System Analysis of an Aero-Engine

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