CFD applications in an aerospace engine test facility

Cooper, G. K.; Phares, W. J.

doi:10.2514/6.1990-2003

Cited by 7 publications

(4 citation statements)

References 1 publication

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“…(2) The pressure at the diffuser exit influences the pressure in the test section through the flow upstream in the thick boundary layer. (3) Increase in total pressure of the flow causes the normal shock to move downstream, as a result the test section pressure will decrease.…”

Section: Case 2 (With Model)mentioning

confidence: 99%

“…3 Among that, high altitude testing (HAT) facility for rocket engines offers the greatest advantage in the ground testing of aerospace engines. 2 Upper stage rocket engines designed for operating at high altitudes need a nozzle with large expansion ratio for the effective utilization of engine pressure. If the nozzles are tested under sea-level conditions then the flow separates near the nozzle wall.…”

Section: Introductionmentioning

confidence: 99%

“…1 Computational fluid dynamics (CFD) has been evolved as an important tool in the design and analysis of aerospace engine ground tests. 2 In the aerospace domain, before rocket propulsion systems are put into operational use, they are subjected to several different types of test facilities. 3 Among that, high altitude testing (HAT) facility for rocket engines offers the greatest advantage in the ground testing of aerospace engines.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A numerical optimization of high altitude testing facility for wind tunnel experiments

Rose

Jinu²,

Brindha

2015

Chinese Journal of Aeronautics

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High altitude test facilities are required to test the high area ratio nozzles operating at the upper stages of rocket in the nozzle full flow conditions. It is typically achieved by creating the ambient pressure equal or less than the nozzle exit pressure. On average, air/GN 2 is used as active gas for ejector system that is stored in the high pressure cylinders. The wind tunnel facilities are used for conducting aerodynamic simulation experiments at/under various flow velocities and operating conditions. However, constructing both of these facilities require more laboratory space and expensive instruments. Because of this demerit, a novel scheme is implemented for conducting wind tunnel experiments by using the existing infrastructure available in the high altitude testing (HAT) facility. This article presents the details about the methods implemented for suitably modifying the sub-scale HAT facility to conduct wind tunnel experiments. Hence, the design of nozzle for required area ratio A/A * , realization of test section and the optimized configuration are focused in the present analysis. Specific insights into various rocket models including high thrust cryogenic engines and their holding mechanisms to conduct wind tunnel experiments in the HAT facility are analyzed. A detailed CFD analysis is done to propose this conversion without affecting the existing functional requirements of the HAT facility.

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Section: Case 2 (With Model)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A numerical optimization of high altitude testing facility for wind tunnel experiments

Rose

Jinu²,

Brindha

2015

Chinese Journal of Aeronautics

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“…Simulated altitude test in ATFs is the most effective and indispensable exploring, debugging, verification and validation means during the development of aero-engine [5][6][7]. According to different flight conditions simulating extents, simulated altitude tests fall into three major categories, direct-connect test, free-jet test and propulsion wind tunnel test [8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility

Zhou

Shen

Zhang

2016

International Journal of Turbo &Amp; Jet-Engines

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Simulated altitude test is an essential exploring, debugging, verification and validation means during the development of aero-engine. Free-jet engine test can simulate actual working conditions of aero-engine more realistically than direct-connect engine test but with relatively lower cost compared to propulsion wind tunnel test, thus becoming an important developing area of simulated altitude test technology. The Flight Conditions Simulating Control System (FCSCS) is of great importance to the Altitude Test Facility (ATF) but the development of that is a huge challenge. Aiming at improving the design efficiency and reducing risks during the development of FCSCS for ATFs, a Hardware-in-the-Loop (HIL) simulation system was designed and the mathematical models of key components such as the pressure stabilizing chamber, free-jet nozzle, control valve and aero-engine were built in this paper. Moreover, some HIL simulation experiments were carried out. The results show that the HIL simulation system designed and established in this paper is reasonable and effective, which can be used to adjust control parameters conveniently and assess the software and hardware in the control system immediately.

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A Sensitivity Equation Approach to Shape Optimization in Fluid Flows

Borggaard

Burns

1995

Flow Control

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In this paper we apply a sensitivity equation method to shape optimization problems. An algorithm is developed and tested on a problem of designing optimal forebody simulators for a 2D, inviscid supersonic flow. The algorithm uses a BFGS/Trust Region optimization scheme with sensitivities computed by numerically approximating the linear partial differential equations that determine the flow sensitivities. Numerical examples are presented to illustrate the method.

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CFD applications in an aerospace engine test facility

Cited by 7 publications

References 1 publication

A numerical optimization of high altitude testing facility for wind tunnel experiments

A numerical optimization of high altitude testing facility for wind tunnel experiments

Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility

A Sensitivity Equation Approach to Shape Optimization in Fluid Flows

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