Integral method for calculating a turbofan engine thrust reverser jet interacting with an external stream

2010 ◽  
Vol 53 (2) ◽  
pp. 212-220
Author(s):  
V. L. Varsegov
Keyword(s):  
Integral Method ◽  
Turbofan Engine ◽  
Engine Thrust ◽  
Thrust Reverser ◽  
External Stream

Generic New Modeling Technique for Turbofan Engine Thrust

2013 ◽  
Vol 29 (6) ◽  
pp. 1492-1495 ◽  
Author(s):  
Luis Fajardo Rodriguez ◽  
Ruxandra Mihaela Botez
Keyword(s):  
Modeling Technique ◽  
Turbofan Engine ◽  
Engine Thrust

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.

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

2012 ◽  
Author(s):  
Tashfeen Mahmood ◽  
Anthony Jackson ◽  
Syed H. Rizvi ◽  
Pericles Pilidis ◽  
Mark Savill ◽  
...  
Keyword(s):  
Engine Performance ◽  
Engine Exhaust ◽  
Turbofan Engine ◽  
The Public ◽  
Engine Model ◽  
Turbine Performance ◽  
Lp Turbine ◽  
Engine Components ◽  
Thrust Reverser ◽  
Bypass Ratio

This paper discusses thrust reverser techniques for a mixed exhaust high bypass ratio turbofan engine and its effect on aircraft and engine performance. The turbofan engine chosen for this study was CUTS_TF (Cranfield University Three Spool Turbofan) which is similar to Rolls-Royce TRENT 772 engine and the information available for this engine in the public domain is used for the engine performance analysis along with the Gas Turbine Performance Software, GasTurb 10. The CUTEA (Cranfield University Twin Engine Aircraft) which is similar to the Airbus A330 is used along side with the engine model for the thrust reverser performance calculations. The aim of this research paper is to investigate the effects on mixed exhaust engine performance due to the pivoting door type thrust reverser deployment. The paper looks into the engine off-design performance characteristics and how the engine components get affected when the thrust reverser come into operation. This includes the changes into the operating point of fan, IP compressor, HP compressor, HP turbine, IP turbine, LP turbine and the engine exhaust nozzle. Also, the reverser deployment effect on aircraft, deceleration time and landing distances are discussed.

scholarly journals Reference and Limit Governors for Limit Protection of Turbofan Engines

Energies ◽  
2019 ◽  
Vol 12 (14) ◽  
pp. 2803 ◽  
Author(s):  
Wenhao Xu ◽  
Muxuan Pan ◽  
Jiakun Qin ◽  
Jinquan Huang
Keyword(s):  
Invariant Sets ◽  
Multiple Constraints ◽  
Turbofan Engine ◽  
Turbofan Engines ◽  
Admissible Sets ◽  
Engine Model ◽  
Engine Control System ◽  
Engine Thrust ◽  
Simulation Results ◽  
Limit Protection

This paper proposes a novel architecture of limit protection including the references governors and limit governors and applies this architecture to limit protection in turbofan engines. References governors are designed as add-on schemes to a pre-stability engine control system that modifies reference commands to avoid constraints violation. Limit governors are proposed as an assistant part for references governors adjusting constraints to prevent references from stopping updates. The use of output admissible sets for a class of variable constraints is exploited to form invariant sets. Simulation results based on a turbofan engine model show that references governors with limit governors can effectively enforce the multiple constraints and provide enhanced engine thrust when steady violation occurs.

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.

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