Aircraft engine thrust reverser

1998 ◽  
Vol 70 (6) ◽  
Keyword(s):  
Aircraft Engine ◽  
Engine Thrust ◽  
Thrust Reverser

A Study of External Fuel Vaporization

1981 ◽  
Author(s):  
E. J. Szetela ◽  
L. Chiappetta ◽  
C. E. Baker
Keyword(s):  
Thermal Stability ◽  
Gas Turbine ◽  
Conceptual Design ◽  
Energy Efficient ◽  
Weight Ratio ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Performance Control ◽  
Engine Thrust ◽  
Fuel Vaporization

A conceptual design study was conducted to devise and evaluate techniques for the external vaporization of fuel for use in an aircraft gas turbine with characteristics similar to the Energy Efficient Engine (E3). A second purpose of the study was to select the most favorable fuel vaporization concept. In the study, three candidate concepts were analyzed from the standpoint of fuel thermal stability, integration of the vaporizer system into the aircraft engine, engine and vaporizer dynamic response, startup and altitude restart, engine performance, control requirements, safety, and maintenance. The results of the study indicate that an external vaporization system can be devised for an E3 -type engine with hardware of reasonable size. The hardware can be packaged without increasing the total engine volume and the system is not unduly complex. The selected concept offers potential gains in engine performance in terms of reduced specific fuel consumption and improved engine thrust/weight ratio. The thrust/weight improvement can be traded against vaporization system weight. However, the vaporizer is subject to fouling with deposits formed at the walls exposed to heated fuel.

Thrust Reverser for a Separate Exhaust High Bypass Ratio Turbofan Engine and its Effect on Aircraft and Engine Performance

2011 ◽  
Author(s):  
Tashfeen Mahmood ◽  
Anthony Jackson ◽  
Vishal Sethi ◽  
Pericles Pilidis
Keyword(s):  
Engine Performance ◽  
Aircraft Engine ◽  
Performance Characteristics ◽  
System Level ◽  
Performance Models ◽  
Turbofan Engine ◽  
Engine Model ◽  
Rate Deceleration ◽  
Thrust Reverser ◽  
Bypass Ratio

This paper discusses thrust reversing techniques for a separate exhaust high bypass ratio turbofan engine and its effect on aircraft and engine performance. Cranfield University is developing suitable thrust reverser performance models. These thrust reverser performance models will subsequently be integrated within the TERA (Techno-economic Environmental Risk Analysis) architecture thereby allowing for more detailed and accurate representations of aircraft and engine performance during the landing phase of a typical civil aircraft mission. The turbofan engine chosen for this study was CUTS_TF (Cranfield University Twin Spool Turbofan) which is similar to the CFM56-5B4 engine and the information available in the public domain is used for the engine performance analysis along with the Gas Turbine Performance Software, ‘GasTurb 10’ [1]. The CUTEA (Cranfield University Twin Engine Aircraft) which is similar to the Airbus A320 is used alongside with the engine model for the thrust reverser performance calculations. The aim of this research paper is to investigate the effects on aircraft and engine performance characteristics due to the pivoting door type thrust reverser deployment. The paper will look into the overall engine performance characteristics and how the engine components get affected when the thrust reversers come into operation. This includes the changes into the operating point of fan, booster, HP compressor, HP turbine, LP turbine, bypass nozzle and core nozzle. Also, thrust reverser performance analyses were performed (at aircraft/engine system level) by varying the reverser exit area by ± 5% and its effect on aircraft deceleration rate, deceleration time and landing distances were observed.

scholarly journals Comparative study on two civil engine thrust reversers for their maintainability analysis

2018 ◽  
Vol 169 ◽  
pp. 01026 ◽  
Author(s):  
Hua-Cong Xu ◽  
Yang Pan ◽  
Yue-Xi Xiong ◽  
Jing-Wu He
Keyword(s):  
Time Estimation ◽  
Selection Scheme ◽  
Engine Thrust ◽  
Trade Offs ◽  
Kinematics Simulation ◽  
Working Principle ◽  
Maintainability Analysis ◽  
Thrust Reverser ◽  
Scheme Analysis ◽  
Virtual Maintenance

Trade-offs studies on two kinds of existing engine thrust reverser design were carried out, applying virtual maintenance method and the basic theory of ergonomics. Analysis on the maintainability of the two kinds of configurations, the O-duct thrust reverser owning the integrated propulsion system (IPS) and the traditional portal D-duct thrust reverser, were compared. According to the differences of O-duct and D-duct thrust reverser in the structure, working principle and mode of motion during the maintenance, structure modelling and kinematics simulation of two kinds of thrust reverser were finished in the same space constraints. Taking DELMIA software as the platform, the partial ergonomic research and evaluation including accessibility analysis, visibility analysis, specific disassembling and assembling time estimation and workspace analysis were put forward through the virtual maintenance simulation of two civil engine thrust reversers. Supplied technical reserves on design and selection, scheme analysis and technical evaluations for domestic engine thrust reverser in the future.

Computational Analysis of Blended Winglet Model Performance by Varying Cant Angle

2019 ◽  
Vol 16 (2) ◽  
pp. 467-471
Author(s):  
Bino Prince D. Raja ◽  
G. Ramanan ◽  
Diju G. Samuel
Keyword(s):  
Fuel Consumption ◽  
Computational Analysis ◽  
Model Performance ◽  
Aircraft Engine ◽  
Modeling And Analysis ◽  
Engine Thrust ◽  
Ansys Cfx ◽  
Inclination Angles ◽  
Important Challenge ◽  
Control Surfaces

This work focuses on structural modeling and analysis of aircraft winglet control surfaces. In aerodynamic engineering, reducing drag is an important challenge. To reduce drag a fin device that is placed vertically in the angle set in the wing of the plane. Winglet design reduces fuel consumption by reducing the drag of the aircraft and will make the aircraft more stable during the flight, will also give the aircraft engine more time to reduce the load on the engine thrust life. The goal is to design and simulate a winglet aircraft model using software such as CATIA V5-which is used to build fin models and ANSYS CFX solver is used to test and simulate model fins. With winglets without fins it analyzes change the inclination angles, the results are compared and plotted. Fins are an important part of an aircraft that reduces the amount of drag and fuel consumption by using less energy while reducing wing vortexes.

Computational fluid dynamics support of the development of a blockerless engine thrust reverser concept

1997 ◽  
Author(s):  
F. Marconi ◽  
B. Gilbert ◽  
R. Tindell ◽  
F. Marconi ◽  
B. Gilbert ◽  
...  
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Engine Thrust ◽  
Thrust Reverser

Aircraft Engine Thrust Estimator Design Based on GSA-LSSVM

2017 ◽  
Vol 34 (3) ◽  
Author(s):  
Hanlin Sheng ◽  
Tianhong Zhang
Keyword(s):  
Gravitational Search Algorithm ◽  
Aircraft Engine ◽  
Least Square ◽  
Integrated Modelling ◽  
Design Solution ◽  
Support Vector ◽  
Engine Thrust ◽  
Thrust Control ◽  
Direct Thrust Control ◽  
Estimator Design

AbstractIn view of the necessity of highly precise and reliable thrust estimator to achieve direct thrust control of aircraft engine, based on support vector regression (SVR), as well as least square support vector machine (LSSVM) and a new optimization algorithm – gravitational search algorithm (GSA), by performing integrated modelling and parameter optimization, a GSA-LSSVM-based thrust estimator design solution is proposed. The results show that compared to particle swarm optimization (PSO) algorithm, GSA can find unknown optimization parameter better and enables the model developed with better prediction and generalization ability. The model can better predict aircraft engine thrust and thus fulfills the need of direct thrust control of aircraft engine.

Advanced Aircraft Engine Microlaminated Intermetallic Composite Turbine Technology

1996 ◽  
Vol 434 ◽  
Author(s):  
R. G. Rowe ◽  
D. W. Skelly ◽  
M. R. Jackson ◽  
M. Larsen ◽  
D. Lachapelle
Keyword(s):  
Low Temperature ◽  
Fracture Resistance ◽  
Physical Vapor Deposition ◽  
Aircraft Engine ◽  
Internal Cooling ◽  
Fine Grain ◽  
Engine Thrust ◽  
Temperature Fracture ◽  
Resistance Curves ◽  
Higher Temperature

AbstractHigher gas path temperatures for greater aircraft engine thrust and efficiency will require both higher temperature gas turbine airfoil materials and optimization of internal cooling technology. Microlaminated composites consisting of very high temperature intermetallic compounds and ductile refractory metals offer a means of achieving higher temperature turbine airfoil capability without sacrificing low temperature fracture resistance. Physical vapor deposition, used to synthesize microlaminated composites, also offers a means of fabricating advanced turbine blade internal cooling designs. The low temperature fracture resistance of microlaminated Nb(Cr)-Cr2Nb microlaminated composites approached 20 MPa√m in fracture resistance curves, but the fine grain size of vapor deposited intermetallics indicates a need to develop creep resistant microstructures.

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