Multiple Segment Parallel Compressor Model for Circumferential Flow Distortion

Mazzawy, R. S.

doi:10.1115/1.3446288

Cited by 98 publications

(57 citation statements)

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“…Historically, in order to provide a simple yet effective model to predict stability margin of a compressor with inlet distortion, many efforts including various small perturbation theories [1] , parallel compressor models [2] , actuator disk theories [3] , and Moore-Greitzer based inertia parameter models [4][5] have been made. Longley et al [6] studied several multistage low-speed compressors with various RID and concluded that the excitation-and-response theory based on the 2D H-G model matched nicely with the test results of those compressors that exhibited only one peak in the response curve of stall margin shift versus distortion rotation speed, but failed to make a good agreement with those machines which had two peaks in the same kind of response curve.…”

Section: Introductionmentioning

confidence: 99%

The role of tip leakage flow in triggering rotating stall of a low speed compressor under inlet distortion

et al. 2009

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The stall behavior in a single-stage low-speed axial compressor under rotating inlet distortion (RID) is investigated in the first half of this paper. The tests demonstrate that the tip leakage flow (TLF) plays an important role in triggering rotating stall. The tracking of the spike-like disturbances caused by the spillage of TLV indicates that most of such spike-like disturbances will be smeared by non-distorted sector and the growth of the spike-like disturbances actually relate closely to how and how often the path of the propagating disturbances come across the path of the rotating distorted sector. In the second half of this paper, micro air injections are applied to test the effect behavior of TLF on stall inception. Contrasts to without micro air injections, the spike-like disturbances are much fewer, so the possibilities that spike-like disturbances may trigger rotating stall are fewer too. As a result, the compressor gets a lower mass flow rate at stall for both co-rotating inlet distortion and counter-rotating inlet distortion.

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Section: Introductionmentioning

confidence: 99%

The role of tip leakage flow in triggering rotating stall of a low speed compressor under inlet distortion

et al. 2009

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“…One of the methods used was a linearized approach (Greitzer 1980;Plourde and Stenning 1967) that provides a quantitative information about the performance of the compressor in a circumferentially non-uniform flow. Several models (Greitzer 1980;Mikolajczak and Pfeffer 1974), such as the parallel compressor model and its extensions (Mazzawy 1977), were used to assess the compressor stability with inlet distortion.…”

Section: Introductionmentioning

confidence: 99%

Study on the propagation of inlet flow distortion in axial compressor using an integral method

Ng¹,

Liu²,

Lim³

et al. 2002

Computational Mechanics

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An integral method is investigated and developed in the current work. The effects of the parameters of inlet distortions on the trend of downstream flow feature in compressor are simulated. Other than the drag-to-lift ratio of the blade and the inlet incidence angle, it is found that the distorted inlet velocity is another essential parameter to control the distortion in propagation. Based on this study, a novel critical distortion line and corresponding critical distortion factor are proposed to express the effect of the two essential inlet parameters on the propagation of distortion, namely, the inlet incidence angle and the distorted inlet velocity. From the viewpoint of compressor efficiency, the propagation of inlet flow distortion is further described by a compressor critical performance and its critical characteristic. The results present a useful physical insight to an axial flow compressor behavior and asymptotic behavior of the propagation of inlet distortion, and confirm the active role of compressor in determining the velocity distribution when compressor responds to an inlet flow distortion.

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“…Physical speed of the gas generator (N) and power turbine (Np) were the control parameters in the steady-state control strategy. (1) where W is mass flow; subscript GT,Cooling is Gas turbine cooling air from compressor.…”

Section: Figure 2 Division Of Circumferential Inlet Flow Distortionmentioning

confidence: 99%

“…Whatever the source, the performance and stability of the aeroengine generally reduced. Even the blade rupture fault occurred when the compressor surged caused by inlet flow distortion [1].…”

Section: Introductionmentioning

confidence: 99%

Performance and Adaptive Surge-Preventing Acceleration Prediction of a Turboshaft Engine under Inlet Flow Distortion

2017

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Abstract. The intention of this paper is to research the inlet flow distortion influence on overall performance of turboshaft engine and put forward a method called Distortion Factor Item (DFI) to improve the fuel supply plan for surge-preventing acceleration when turboshaft engine suddenly encounters inlet flow distortion. Based on the parallel compressor theory, steady-state and transition-state numerical simulation model of turboshaft engine with subcompressor model were established for researching the influence of inlet flow distortion on turboshaft engine. This paper made a detailed analysis on the compressor operation from the aspects of performance and stability, and then analyzed the overall performance and dynamic response of the whole engine under inlet flow distortion. Improved fuel supply plan with DFI method was applied to control the acceleration process adaptively when encountering different inlet flow distortion. Several simulation examples about extreme natural environments were calculated to testify DFI method's environmental applicability. The result shows that the inlet flow distortion reduces the air inflow and decreases the surge margin of compressor, and increase the engine exhaust loss. Encountering inlet flow distortion has many adverse influences such as sudden rotor acceleration, turbine inlet temperature rise and power output reduction. By using improved fuel supply plan with DFI, turboshaft engine above-idle acceleration can avoid surge effectively under inlet flow distortion with environmental applicability.

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Multiple Segment Parallel Compressor Model for Circumferential Flow Distortion

Cited by 98 publications

References 0 publications

The role of tip leakage flow in triggering rotating stall of a low speed compressor under inlet distortion

The role of tip leakage flow in triggering rotating stall of a low speed compressor under inlet distortion

Study on the propagation of inlet flow distortion in axial compressor using an integral method

Performance and Adaptive Surge-Preventing Acceleration Prediction of a Turboshaft Engine under Inlet Flow Distortion

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