The effect of inlet temperature and pressure distortion on turbojet performance

Braithwaite, W. M.; Graber, E. J.; Mehalic, C. M.

doi:10.2514/6.1973-1316

Cited by 17 publications

(12 citation statements)

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“…The effect of circumferential distortion on gas turbine performance was investigated by Calogeras et al [9] and Milner and Wenzel [10], who presented the operating line shift of a J85-GE-13 turbojet, under various distortion patterns. The stability of the same engine under combined inlet temperature and pressure distortion was consequently studied by Braithwaite et al [11]. In the same study the application of a parallel compressor model showed a reasonable agreement with the experiment.…”

Section: Introductionmentioning

confidence: 73%

“…It becomes apparent that increasing critical angle results in rising surge pressure ratio and reducing surge mass flow. It was, therefore, decided to express overall deviation as the sum of relative errors using (11). This approach resulted in a clear optimum region, as shown in Figure 8, where the sum of mass and pressure ratio deviations has been plotted against "θ crit ".…”

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confidence: 99%

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Development of a Method for Enhanced Fan Representation in Gas Turbine Modeling

Doulgeris

Khaleghi

Kalfas

et al. 2011

International Journal of Rotating Machinery

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A challenge in civil aviation future propulsion systems is expected to be the integration with the airframe, coming as a result of increasing bypass ratio or above wing installations for noise mitigation. The resulting highly distorted inlet flows to the engine make a clear demand for advanced gas turbine performance prediction models. Since the dawn of jet engine, several models have been proposed, and the present work comes to add a model that combines two well-established compressor performance methods in order to create a quasi-three-dimensional representation of the fan of a modern turbofan. A streamline curvature model is coupled to a parallel compressor method, covering radial and circumferential directions, respectively. Model testing has shown a close agreement to experimental data, making it a good candidate for assessing the loss of surge margin on a high bypass ratio turbofan, semiembedded on the upper surface of a broad wing airframe.

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Section: Introductionmentioning

confidence: 73%

mentioning

confidence: 99%

Development of a Method for Enhanced Fan Representation in Gas Turbine Modeling

Doulgeris

Khaleghi

Kalfas

et al. 2011

International Journal of Rotating Machinery

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“…The compressor-outlet profiles show very little circumferential variation in the total/ static pressure; however, a total temperature distortion is evident. If the region of higher exit temperature is the result of the higher compression heat in the distorted sector, distorted flow rotates approximately 90°in the rotor-rotating direction passing from the low-pressure sector of the compressor inlet to the compressor outlet [18].…”

Section: Verification Of the Numerical Simulation Methodsmentioning

confidence: 99%

“…The pressure distortion is not constant with airflow. The pressure distortion for screen "A" varies from 5% at 90% of the speed to 12% at the rated speed [18].…”

Section: Verification Of the Numerical Simulation Methodsmentioning

confidence: 99%

The Influences of Combined Distortions on Fan Performance

Quanyong¹,

Honghu²,

Hou³

2023

Advances in Turbomachinery

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Combined distortions negatively affect the aerodynamic stability of fans, but previous studies have limitations. The 3D CFD method was used to calculate the aerodynamic stability of fans under the total pressure and swirl distortion, total temperature and swirl distortion, and total pressure and total temperature distortion in the work. Rotor 67 was taken as the research object. According to the calculation results, the influences of variable distortion parameters on fan performance under combined distortions were summarized to establish the functional relationship between stability margin losses and distortion parameters.

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“…Previous work has shown the effects of total pressure distortion on turbofan engines, and both pressure and temperature distortions on turbojet engines. 9 ' 11 An experimental program was conducted using a TF30-P-3 turbofan engine to obtain better definition of the flow ahead of the inlet and through the compressor system. In addition, it was desired to evaluate the effectiveness of the model in predicting the flow characteristics with combined pressure and temperature distortions.…”

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confidence: 99%