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.

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.

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.

Performance prediction and progress towards multi-disciplinary design of contra-rotating open rotors

2014 ◽  
Vol 118 (1208) ◽  
pp. 1159-1179 ◽  
Author(s):  
S. Guérin ◽  
R. Schnell ◽  
R. G. Becker
Keyword(s):  
Experimental Data ◽  
Wind Tunnel ◽  
Environmental Impact ◽  
Performance Prediction ◽  
Engine Performance ◽  
Turbofan Engines ◽  
Prediction Tools ◽  
First Results ◽  
Open Rotor ◽  
Bypass Ratio

Abstract At DLR’s Institute of Propulsion Technology, the prediction tools and multi-disciplinary optimisation strategies developed for turbofan engines have been extended to contra-rotating open rotors (CROR). Thereby the objective has been to appraise and improve the performance of CROR engines and thus to reduce their environmental impact. The present paper reviews the intermediate progress achieved in this scope. The prediction is based on analytical and CFD methods and covers the fields of engine performance analysis, aerodynamics and acoustics. The aerodynamic and acoustic results could be partly validated through the comparison to experimental data obtained from wind-tunnel tests. In a multi-disciplinary approach the aforementioned aspects are optimised together. First results of an aero-acoustic optimisation are presented. Furthermore this paper undertakes some comparison between high-bypass ratio turbofan engines and open-rotor concepts.

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.

Fluidic Injection Thrust Reverser System for High Bypass Ratio Turbofan Engines: Experimental Model

2020 ◽  
Author(s):  
Raghav Kumar ◽  
Pankaj Rajput ◽  
Sunil Kumar
Keyword(s):  
Experimental Model ◽  
Computational Analysis ◽  
Core Flow ◽  
Turbofan Engines ◽  
The Core ◽  
Engine Thrust ◽  
3D Printed ◽  
Heavy Loads ◽  
Thrust Reverser ◽  
Bypass Ratio

Abstract Conventional thrust reversers involve the usage of mechanical blockers which are bulky as they are designed to sustain heavy loads. As a result, they account for 30% of the nacelle weight (excluding the engine core). This added engine weight results in a 0.5%–1% increase in the specific fuel consumption of the aircraft. This paper advances our investigation of “Blockerless Engine Thrust Reversers” and uses it as an inspiration to optimize the system by designing an injection module (depicting an injection as a bleed from the core flow), conducting a computational analysis and demonstrating the viability of the process by building an experimental model of a 1:40 scale of a GE90 - 115B engine. A 3D printed experimental model was built after conducting an extensive parametric analysis. This model is used to demonstrate the viability of the “Fluidic Injection Thrust Reverser” (FITR) qualitatively and quantitatively.

Open Rotor Engine Cycle Modeling and Performance Assessment

2020 ◽  
Author(s):  
Ziyu Zhang ◽  
Li Zhou ◽  
Xiaobo Zhang ◽  
Zhanxue Wang
Keyword(s):  
Engine Performance ◽  
Performance Model ◽  
Civil Aviation ◽  
Environment Impact ◽  
Turbine Performance ◽  
New Concepts ◽  
Open Rotor ◽  
Potential Impact ◽  
And Performance ◽  
Bypass Ratio

Abstract Aiming to enable dramatic reductions in the environment impact and fuel consumption of future civil aviation, NASA and European related research institutions are committed to developing new concepts and technologies in which counter rotating open rotor (CROR) concept can achieve this objective. In order to evaluate its potential impact, an open rotor engine performance model needs to be established. This paper presents the modeling method of an open rotor engine with the geared counter rotating open rotor (GOR) as object, and implements it in an in-house modular program of gas turbine performance prediction. In addition, the steady-state performance of the model is analyzed, and the model accuracy is verified based on the existing data. On this basis, the performance of open rotor engine and high bypass ratio turbofan engine is compared and results show that the counter rotating open rotor engine has obvious fuel saving advantages.

scholarly journals CFD Study of Nozzle Configurations for Ultra High Bypass Engines

1993 ◽  
Author(s):  
H. Zimmermann ◽  
R. Gumucio ◽  
K. Katheder ◽  
A. Jula
Keyword(s):  
Engine Performance ◽  
Operating Conditions ◽  
Aerodynamic Design ◽  
Thrust Coefficient ◽  
Optimum Range ◽  
Installation Effects ◽  
Wide Range ◽  
And Performance ◽  
Aircraft Aerodynamics ◽  
Bypass Ratio

Performance and aerodynamic aspects of ultra-high bypass ratio ducted engines have been investigated with an emphasis on nozzle aerodynamics. The interference with aircraft aerodynamics could not be covered. Numerical methods were used for aerodynamic investigations of geometrically different aft end configurations for bypass ratios between 12 and 18, this is the optimum range for long missions which will be important for future civil engine applications. Results are presented for a wide range of operating conditions and effects on engine performance are discussed. The limitations for higher bypass ratios than 12 to 18 do not come from nozzle aerodynamics but from installation effects. It is shown that using CFD and performance calculations an improved aerodynamic design can be achieved. Based on existing correlations, for thrust and mass-flow, or using aerodynamic tailoring by CFD and including performance investigations, it is possible to increase the thrust coefficient up to 1%.

Performance Improvement Through Indexing of Turbine Airfoils: Part 1 — Experimental Investigation

1995 ◽  
Author(s):  
F. W. Huber ◽  
P. D. Johnson ◽  
O. P. Sharma ◽  
J. B. Staubach ◽  
S. W. Gaddis
Keyword(s):  
Performance Improvement ◽  
Space Shuttle ◽  
Computational Procedure ◽  
Analytical Investigation ◽  
Test Facility ◽  
Test Article ◽  
Performance Improvements ◽  
Turbine Stator ◽  
Turbine Performance ◽  
Cfd Analyses

This paper describes the results of a study to determine the performance improvements achievable by circumferentially indexing successive rows of turbine stator airfoils. An experimental / analytical investigation has been completed which indicates significant stage efficiency increases can be attained through application of this airfoil clocking concept. A series of tests was conducted at the National Aeronautics and Space Administration’s (NASA) Marshall Space Flight Center (MSFC) to experimentally investigate stator wake clocking effects on the performance of the Space Shuttle Main Engine Alternate Fuel Turbopump Turbine Test Article. Extensive time-accurate Computational Fluid Dynamics (CFD) simulations have been completed for the test configurations. The CFD results provide insight into the performance improvement mechanism. Part one of this paper describes details of the test facility, rig geometry, instrumentation, and aerodynamic operating parameters. Results of turbine testing at the aerodynamic design point are presented for six circumferential positions of the first stage stator, along with a description of the initial CFD analyses performed for the test article. It should be noted that first vane positions 1 and 6 produced identical first to second vane indexing. Results obtained from off-design testing of the “best” and “worst” stator clocking positions, and testing over a range of Reynolds numbers are also presented. Part two of this paper describes the numerical simulations performed in support of the experimental test program described in part one. Time-accurate Navier-Stokes flow analyses have been completed for the five different turbine stator positions tested. Details of the computational procedure and results are presented. Analysis results include predictions of instantaneous and time-average mid-span airfoil and turbine performance, as well as gas conditions throughout the flow field. An initial understanding of the turbine performance improvement mechanism is described.

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.

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