Effect of spatial inlet temperature and pressure distortion on turbofan engine stability

Mehalic, C. M.

doi:10.2514/6.1988-3016

Cited by 11 publications

(3 citation statements)

References 2 publications

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“…When the low-pressure zone coincides with the high-temperature zone, it will cause the high-pressure compressor to stall. When the low-pressure zone is opposite to the high-temperature zone, the influence on the stability of the highpressure compressor will be weakened [3]. Davis used a stage-by-stage parallel compression system simulation and found the largest loss in stall-margin results under the steady-state pressure and temperature distortion when the high-temperature and lowpressure regions coincide.…”

Section: Introductionmentioning

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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Section: Introductionmentioning

confidence: 99%

The Influences of Combined Distortions on Fan Performance

Quanyong¹,

Honghu²,

Hou³

2023

Advances in Turbomachinery

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“…2 Similarly, nonuniform distribution of the total temperature at the same area denotes the presence of total temperature distortion and may occur due to the ingestion of exhaust gases from a leading aircraft or a fired missile. 3 As these distorted airflow conditions reach the aerodynamic interface plane (AIP), which is the boundary between the intake and the engine, they start affecting the operation of the entire powerplant.…”

Section: Introductionmentioning

confidence: 99%

Stability assessment of an airflow distorted military engine’s FAN

Triantafyllou

Nikolaidis

Diakostefanis

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Military aircraft are often subjected to severe flight maneuvers with high Angles of Attack (AOA) and Angles of Sideslip (AOSS). These flight attitudes induce non-uniformity in flow conditions to their gas turbine engines which may include distortion of inlet total pressure and total temperature at the Aerodynamic Interface Plane (AIP). Operation of the downstream engine's compression system may suffer reduced aerodynamic performance and stall margin, and increased blade stress levels. The present study presents a methodology of evaluating the effect of inlet flow distortion on the engine's fan stability. The flow distortion examined was induced to the AIP by means of changing the aircraft's flight attitude. The study is based on the steady state flow results from 27 different flight scenarios that have been simulated in CFD. As a baseline model geometry an airframe inspired by the General Dynamics/LMAERO F-16 aircraft was chosen, which has been exposed to subsonic incoming airflow with varying direction resembling thus different aircraft flight attitudes. The results are focused on the total pressure distribution on the engine's (AIP) face and how this is manifested at the operation of the fan. Based on the results, it was concluded that the distorted conditions cause a shift of the surge line on the fan map, with the amount of shift to be directly related to the severity of these distorted conditions. The most severe flight attitude in terms of total pressure distortion, among the tested ones, caused about 7% surge margin depletion comparing to the undistorted value.

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“…9) and PW1128 low-bypass turbofan (Ref. 10) was that inlet distortion modifies the compression system performance maps, adversely shifting the surge lines. It is also known that inlet distortions are attenuated as they travel through the engine compression system (Ref.…”

Section: Introductionmentioning

confidence: 99%