Optimisation of a Thrust Reverser Cascade: An Assessment of Dynamic Response During Reverse Thrust

2003 ◽  
Author(s):  
J Butterfield ◽  
H Yao ◽  
E Benard ◽  
M Price ◽  
R Cooper ◽  
...  
Keyword(s):  
Dynamic Response ◽  
Thrust Reverser ◽  
Reverse Thrust

Investigation on a Blockerless Cascade Thrust Reverser System Based on Response Surface Method

2018 ◽  
Author(s):  
Li Zhou ◽  
Zhanxue Wang ◽  
Jingwei Shi ◽  
Xiaobo Zhang
Keyword(s):  
High Pressure ◽  
Secondary Flow ◽  
Response Surface ◽  
Response Surface Method ◽  
Interaction Effect ◽  
Pressure Ratio ◽  
Surface Method ◽  
Thrust Reverser ◽  
Reverse Thrust ◽  
Secondary Injection

The blockerless cascade thrust reverser is one of the innovative thrust reverser systems, which replaces the traditionally mechanical blocker door with the aerodynamic blocker door by high-pressure secondary injection, thus significantly reduces the nacelle weight and the complexity of the actuator, and especially suitable for high-bypass-ratio turbofan engine. In order to obtain the optimum performance of a blockerless cascade thrust reverser system and provide the guidance for the design of the blockerless cascade thrust reverser system, a blockerless cascade thrust reverser system was studied in this paper based on the Response Surface Method (RSM), focusing on the effect of different geometric and aerodynamic parameters on the thrust reverser performance. Results show that the secondary injection with high pressure forms the blockage effect to the fan flow, then forces the fan flow to deflect and discharge from the cascade window, realizing the reverse thrust. The thrust reverser performance is mainly affected by fan pressure ratio (FPR), secondary flow pressure ratio (SPR), secondary injection position (Xjet), secondary injection angle (αjet) and cascade installation angle (β), and the dominated factors are FPR, SPR and Xjet. According to the obtained response equation of the thrust reverser performance, the relationship between reverse thrust efficiency and various parameters are clearly described, and performance of thrust reverser can be quickly evaluated. Significant interaction effects exist between different two factors, which must be taken into consideration in the design process of the blockerless cascade thrust reverser system, especially for the interaction effect between FPR and Xjet, interaction effect between FPR and β. Optimization design with objective of maximum reverse thrust was carried out to determine the best parameter settings, and reverse thrust ratio ηTrev of 60% is achieved under the constraint of the secondary flow ratio.

Navier-Stokes Computation on a Pivoting Doors Thrust Reverser and Comparison With Tests

1992 ◽  
Author(s):  
L. Schreiber ◽  
M. Legras
Keyword(s):  
Flow Field ◽  
Complex Geometry ◽  
Numerical Data ◽  
Navier Stokes ◽  
Complex Flow ◽  
Static Test ◽  
Development Delay ◽  
Cfd Method ◽  
Thrust Reverser ◽  
Reverse Thrust

An engine thrust reverser must meet different aerodynamic requirements to take into account the engine and airplane integration. These requirements are: - Control of the exit area in order to assess a convenient engine compatibility during the reverser operation. - Generation of reverse thrust meeting the level specified by the airframe in order to slowdown the airplane. - Mimization of the reversed flow field interaction with the airplane structure such as wing and shutters. - Avoid the flow reingestion by the engine fan. In order to reduce the tests number, to decrease the development delay and to improve aerodynamic performance, SNECMA group (SNECMA and HISPANO-SUIZA) has decided to develop a CFD method adapted to pivoting doors thrust reverser aerodynamic calculation. This method uses a Navier-Stokes 3D solver (PHOENICS code) well adapted to complex geometry and complex flow field. The mesh is generated with an analytical method and only one domain is used. The computation has been completed assuming laminar viscosity. The numerical data got with this method have been compared to static test realized on a model similar to actual CFM56-5C four doors reverser. The comparison parameters are the static pressure on the doors, the flow rate and the axial reverse thrust.

scholarly journals Enhancement of thrust reverser cascade performance using aerodynamic and structural integration

2004 ◽  
Vol 108 (1090) ◽  
pp. 621-628 ◽  
Author(s):  
J. Butterfield ◽  
H. Yao ◽  
M. Price ◽  
C. Armstrong ◽  
S. Raghunathan ◽  
...  
Keyword(s):  
Structural Model ◽  
Three Dimensional ◽  
Operating Conditions ◽  
Product Development Process ◽  
Structural Performance ◽  
Two Dimensional ◽  
Operational Conditions ◽  
Structural Integration ◽  
Thrust Reverser ◽  
Reverse Thrust

AbstractThis paper focuses on the design of a cascade within a cold stream thrust reverser during the early, conceptual stage of the product development process. A reliable procedure is developed for the exchange of geometric and load data between a two dimensional aerodynamic model and a three dimensional structural model. Aerodynamic and structural simulations are carried out using realistic operating conditions, for three different design configurations with a view to minimising weight for equivalent or improved aerodynamic and structural performance. For normal operational conditions the simulations show that total reverse thrust is unaffected when the performance of the deformed vanes is compared to the un-deformed case. This shows that for the conditions tested, the minimal deformation of the cascade vanes has no significant affect on aerodynamic efficiency and that there is scope for reducing the weight of the cascade. The pressure distribution through a two dimensional thrust reverser section is determined for two additional cascade vane configurations and it is shown that with a small decrease in total reverse thrust, it is possible to reduce weight and eliminate supersonic flow regimes through the nacelle section. By increasing vane sections in high pressure areas and decreasing sections in low pressure areas the structural performance of the cascade vanes in the weight reduced designs, is improved with significantly reduced levels of vane displacement and stress.

Thrust Reverser Catchers: Devices Which Enable Cyclic Testing Between Forward and Reverse Thrust

1996 ◽  
Author(s):  
Richard C. Adkins ◽  
Mike Sherwood
Keyword(s):  
Cyclic Testing ◽  
Exhaust Gases ◽  
Cyclic Operation ◽  
Test Cells ◽  
Thrust Reverser ◽  
Reverse Thrust ◽  
Complicated Nature

Cyclic operation of engines between forward and reverse thrust configurations is a requirement of testing for Extended Twin Operations (ETOPS) certification. When these tests are conducted inside enclosed test cells it is then necessary to redirect the exhaust gases in order to return them to the cell exhaust ducting. This is done by specially designed catcher ducts which have undergone many years of development, due to the complicated nature of the flow. The paper discusses the features that have eventually made these devices successful and as such is intended as an aid to design.

Computational and Experimental Investigation of Unsteady and Acoustic Characteristics of Counter-Rotating Fans

2004 ◽  
Author(s):  
I. A. Brailko ◽  
V. I. Mileshin ◽  
M. A. Nyukhtikov ◽  
S. V. Pankov
Keyword(s):  
Large Angle ◽  
Experimental Investigations ◽  
Acoustic Characteristics ◽  
Optimal Position ◽  
Valuable Property ◽  
Main Thing ◽  
Thrust Reverser ◽  
Reverse Thrust ◽  
Bypass Ratio ◽  
Radial Axis

The matter of developing counter-rotating fans for advanced next generation aeroengines with ducted and unducted propfans is very important [1]. Counter-rotating fans can be made with fixed blades. This article considers tractor propfans consisting of two counter-rotating rotors of variable pitch (VPR) which valuable property is the possibility to turn their blades about the radial axis in order they can take the optimal position in direct thrust regimes, and to obtain a reverse thrust when turning them by a rather large angle. In this case there is no necessity to use a bulky special clamshell-type thrust reverser. In the 1-st phase of designing new CRFs it is necessary, by calculation or experimentally, to show the possibility of obtaining gasdynamic effectiveness of such fans up to the level of single-rotor fans or, at least, to obtain η*ad.f ≥ 0.90÷0.91. But the main thing is to substantiate the feasibility of getting high acoustic characteristics. CIAM (Central Institute of Aviation Motors) is carrying out calculation-experimental investigations of the SV-92 ducted counter-rotating propfan (DCRP) model (the SV-92 is an advanced fan for ultra-high bypass ratio engine [2]) as well as the SV-27 CRF (Fig. 1, Table 1) with unducted rotors for the test aircraft. This paper presents some results on gasdynamic and acoustic characteristics for the SV-27 CRF only. These investigations are aimed at providing the meeting of the test aircraft perceivable noise to ICAO chapter IV regulations.

Design Feasibility of Annular Target Thrust Reversers

2012 ◽  
Author(s):  
Enaut Gonzalez-Ruiz ◽  
Tashfeen Mahmood ◽  
Vishal Sethi ◽  
Pericles Pilidis
Keyword(s):  
Engine Performance ◽  
Advisory Council ◽  
The Public ◽  
Turbofan Engines ◽  
Turbine Performance ◽  
Fluent Software ◽  
Cfd Analyses ◽  
Thrust Reverser ◽  
Reverse Thrust ◽  
Bypass Ratio

Concerns for ecological aviation products and the objective of reducing pollutants to meet ACARE (Advisory Council for Aeronautics Research in Europe) targets address, among other initiatives, the necessity of reducing the overall weight of the aircraft. One way of dealing with the problem of aircraft weight is by investigating thrust reversers. Reducing the reverser weight will have favourable effects on fuel consumption and CO2 emissions. This paper discusses the target type thrust reverser concept. This concept was proposed by NASA and has a potential of reducing the reverser weight on future high bypass ratio turbofan engines. A feasibility study of the annular target thrust reverser in terms of engine performance and reverse thrust achieved was carried out. It comprises 2D CFD analyses of the thrust reverser and the effect of the reverser on the engine performance for different deflector configurations. The turbofan engine chosen for this study is CUTS_TF (Cranfield University Twin Spool Turbo Fan) which is similar to the GE90-85B and the information available in the public domain [1] [2] is used for the engine performance analysis along with the gas turbine performance software, GasTurb 10 [3]. CFD analyses were performed using the FLUENT software [4] to investigate the thrust reverser flow dynamics at landing at maximum reverse thrust.

Human pilot dynamic response in flight and simulator.

1958 ◽  
Author(s):  
Edward Seckel ◽  
Ian A. M. Hall ◽  
Duane T. McRuer ◽  
David H. Weir
Keyword(s):  
Dynamic Response
Sign in / Sign up

Export Citation Format

Share Document