Pre-Stall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation

Chen, Jen‐Ping; Hathaway, Michael D.; Herrick, Gregory P.

doi:10.1115/gt2007-27926

Cited by 24 publications

(7 citation statements)

References 29 publications

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“…In addition, the hypothesis that the stall is initiated by the LE spillage of the interface is strongly supported by numerical and experimental results. 15–18 The phenomena of the backflow at the TE plane are also observed in the stall process. 18,19–21 Hoying et al.…”

Section: Introductionmentioning

confidence: 97%

Numerical study of the unsteady behaviors and rotating stall inception process in a counter-rotating axial compressor

Mao

Liu

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Unsteady computations of a counter-rotating axial compressor are performed and analyzed to investigate the unsteady behaviors in the compressor and the role of the tip leakage flow together with the rotating stall inception process. The results show that the oscillation on the pressure side is much stronger than that on the suction surface for both rotors, especially near the tip region where the trajectory of the tip leakage vortex (TLV) interacts with the blades most often. There exists a periodical leading edge spillage of the interface in rotor2 due to the unsteadiness of tip leakage flow (TLF) at near-stall condition. The blockage generated by the TLV increases dramatically due to the increasing strength of the TLV and the backflow phenomenon as the mass flow decreased. The appearance of the frequency components of 0.5 blade passing frequency (BPF) and 1.5BPF from 0.64BPF can be viewed as the rotating stall inception warning. The fluctuation strength of oscillation frequencies of 0.5BPF and 1.5BPF decreases rapidly from leading edge to trailing edge in rotor2, which indicates that the unsteady fluctuation of TLF at the leading edge in rotor2 is responsible for the stall inception of the compressor. Additionally, both the leading edge spillage and trailing edge backflow phenomena are observed for spike initiated rotating stall at stall point.

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Section: Introductionmentioning

confidence: 97%

Numerical study of the unsteady behaviors and rotating stall inception process in a counter-rotating axial compressor

Mao

Liu

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…There are many computational efforts in simulating the stallinception process in axial compressors [17][18][19][20], each of which possesses different approaches with their own research goals. For example, in the most recent work of Davis and Yao [20], a timeaccurate single-blade-passage multiblade-row strategy is used to simulate the high-frequency unsteadiness due to self-excited flow at scales of the blade passage and rotor tip clearance as well as lowfrequency unsteadiness due to longitudinal system modes.…”

Section: Computational Approachmentioning

confidence: 99%

“…It is not unexpected that unsteady numerical simulation of a stalled compressor requires a great deal of computational resources. Chen and Hathaway [17] presented such an example, in which the simulations were run on an IBM P4 cluster at the Naval Oceanographic Office Major Shared Resource Center using 328 CPUs with 24 h (wall clock) computation time for one rotor revolution. There are 94 blade passages for the entire grid, with a total of 67 million grid points.…”

Section: Computational Approachmentioning

confidence: 99%

Flow Structure of Short-Length-Scale Disturbance in an Axial-Flow Compressor

Feng

Zhang

Chen

et al. 2008

Journal of Propulsion and Power

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Short-length-scale disturbances, also called spikes, are often responsible in triggering rotating stall in axial-flow compressors. One hypothesis suggests that spikes can be the consequence of dynamic interaction among forwardspilled tip-leakage flow, the main throughflow, and the reversed flow. However, the transit process of such a dynamic interaction in the vicinity of the rotor tip clearance and, thus, the physical images of the flow structure of a spike are still unknown. In this paper, we present a numerical study with a novel scheme for a low-speed axial-flow compressor by incorporating rotating inlet distortion. Because the inlet distortion will overload a portion of the blades while keeping the rest working normally, the short-length-scale disturbances can be observed without advocating the computational difficulty of simulating a fully stalled compressor. Two unsteady simulations using a commercial, three-dimensional, time-accurate, Reynolds-averaged Navier-Stokes solver are performed: one for a one-fourth rotor annulus with finer grids and the other for the entire rotor annulus with coarser grids. After the code is validated by comparing experimental results with the simulation for the entire rotor annulus, the one-fourth-annulus simulation is used to unveil the flow physics. As elucidated from the computational results, the complete birth-todecay process of the short-length-scale disturbances is captured for the first time. The corresponding 3-D flow structure is also revealed. It is shown that the effects of dynamic flow interaction at the tip extend beyond the tip region and deeply into the blade span. A horn-shaped vortex with one end at about 30% of the blade span and the other end at the casing is formed, which generates a low-pressure dip in the casing-pressure measurement. The spike, as identified from casing-pressure measurement, corresponds to a flow image in which the vortex rotates around the annulus.

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“…modal-and spike-type stall inception. In the case of transonic compressors, Chen et al 13 and Gannon et al 14 find a combination of modal-and spike-type stall inception.…”

Section: Introductionmentioning

confidence: 99%

Unsteady wall pressure measurement in a one-and-a-half stage axial transonic compressor during stall inception

Biela

Brandstetter

Schiffer

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part A:

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This paper presents the experimental investigation of the stall inception of a state-of-the-art transonic compressor that resembles a typical front stage of a commercial jet engine. The compressor was designed and manufactured in cooperation with Rolls-Royce Deutschland and assembled in the Darmstadt Transonic Compressor test facility at Technische Universität Darmstadt, Germany. Utilising the 1.5-stage design it is possible to investigate stall inception for different rotor inflow conditions. The aerodynamic features prior and during stall inception are investigated by means of unsteady pressure probes in the casing above the rotor. All stall inception events have a spike-type stall character. However, in some cases the spikes are preceded by modal-type activities. In addition to the unsteady wall pressure, speed lines are presented. The combination of the data shows a clear effect of measurement position and averaging process on the shapes of the speed lines but did not allow to predict the type of stall inception.

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Pre-Stall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation

Cited by 24 publications

References 29 publications

Numerical study of the unsteady behaviors and rotating stall inception process in a counter-rotating axial compressor

Numerical study of the unsteady behaviors and rotating stall inception process in a counter-rotating axial compressor

Flow Structure of Short-Length-Scale Disturbance in an Axial-Flow Compressor

Unsteady wall pressure measurement in a one-and-a-half stage axial transonic compressor during stall inception

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