Rotor Blade Unsteady Aerodynamic Gust Response to Inlet Guide Vane Wakes

Manwaring, Steven R.; Fleeter, Sanford

doi:10.1115/91-gt-129

Cited by 4 publications

(1 citation statement)

References 6 publications

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“…Manwaring et al. 40 carried out experiment on an axial flow compressor and measured the first harmonic gust components. Analysis of forcing function showed that the transverse harmonic gust amplitudes became smaller, while the streamwise harmonic gust amplitudes became larger as the gust amplitude ratio increased.…”

Section: Performance Of Compressor and Pump With Igvsmentioning

confidence: 99%

A review of prewhirl regulation by inlet guide vanes for compressor and pump

Liu

Tan

Cao

2018

Proceedings of the Institution of Mechanical Engineers, Part A:

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To achieve the energy conservation and sustainable development, the prewhirl regulation by inlet guide vanes is proposed and rapidly developed for the compressor and pump. The inlet guide vanes change the flow pattern at the impeller inlet especially the velocity circulation, and then influence the performance of compressor and pump. This paper presents and discusses researches on the prewhirl regulation by inlet guide vanes. Researches include mechanism analysis of prewhirl regulation, experimental and numerical studies on the flow field, performance of compressor and pump with inlet guide vanes, influence of geometric parameters on performance of inlet guide vanes, and failure mode analysis and corresponding flow control methods.

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Section: Performance Of Compressor and Pump With Igvsmentioning

confidence: 99%

A review of prewhirl regulation by inlet guide vanes for compressor and pump

Liu

Tan

Cao

2018

Proceedings of the Institution of Mechanical Engineers, Part A:

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An Analysis System for Blade Forced Response

Chiang¹,

Kielb²

1992

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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A frequent cause of turbomachinery blade failure is excessive resonant response. The most common excitation source is the nonuniform flow field generated by inlet distortion, wakes, and/or pressure disturbances from adjacent blade rows. The standard method for dealing with this problem is to avoid resonant conditions using a Campbell diagram. Unfortunately, it is impossible to avoid all resonant conditions. Therefore, judgements based on past experience are used to determine the acceptability of a blade design. A new analysis system has been developed to predict blade forced response. The system provides a design tool, over and above the standard Campbell diagram approach, for predicting potential forced response problems. The incoming excitation sources are modeled using a semi-empirical rotor wake/vortex model for wake excitation, measured data for inlet distortion, and a quasi-3D Euler code for pressure disturbances. Using these aerodynamic stimuli, and the blade’s natural frequencies and mode shapes from a finite element model, the unsteady aerodynamic modal forces and the aerodynamic damping are calculated. A modal response solution is then performed. This system has been applied to current engine designs. A recent investigation involved fan blade response due to inlet distortion. An aeromechanical test had been run with two different distortion screens. The resulting distortion entering the fan was measured. With this as input data, the predicted response agreed almost exactly with the measured response. In another application, the response of the LPT blades of a counter-rotating supersonic turbine was determined. In this case the blades were excited by both a wake and a shock wave. The shock response was predicted to be three times larger than that of the wake. Thus, the system identified a new forcing function mechanism for supersonic turbines. This paper provides a basic description of the system, which includes: 1) models for the wake excitation, inlet distortion, and pressure disturbance; 2) a kernel function solution technique for unsteady aerodynamics; and 3) a modal aeroelastic solution using strip theory. Also, results of the two applications are presented.

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Turbine and Compressor Wake Modeling for Blade Forced Response

Izsak¹,

Chiang²

1993

Volume 3A: General

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A key ingredient in turbine and compressor forced response analyses is the prediction of wake strength. An empirical wake model and a 3D CFD flow solver have been used for this purpose. The empirical wake model predictions were compared with wake data obtained from low speed turbine and compressor rigs, and from a high speed turbine facility for a high pressure turbine nozzle with cooling flows. The CFD flow solver is used to predict the turbine low speed and high speed wakes, and to provide a basis of comparison for transonic fan wakes. The wake data and predictions were Fourier decomposed to compare the harmonic content of the wakes. Although the empirical wake model adequately predicts the compressor wakes, turbine wake predictions need improvements. The CFD wake model needs additional data for calibration, in particular with regard to turbulence and transition. This paper provides a guide for applying empirical and CFD methods to model turbine and compressor wakes for blade forced response analysis.

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Rotor Blade Unsteady Aerodynamic Gust Response to Inlet Guide Vane Wakes

Cited by 4 publications

References 6 publications

A review of prewhirl regulation by inlet guide vanes for compressor and pump

A review of prewhirl regulation by inlet guide vanes for compressor and pump

An Analysis System for Blade Forced Response

Turbine and Compressor Wake Modeling for Blade Forced Response

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