Experimental Investigation of the Rotor-Stator Interactions Within a High Speed, Multi-Stage, Axial Compressor: Part 1 — Experimental Facilities and Results

Arnaud, David; Ottavy, Xavier; Vouillarmet, André

doi:10.1115/gt2004-53764

Cited by 9 publications

(6 citation statements)

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“…In order to have traversing probes between blade and vane rows, the axial gap was slightly increased compared to current compressors. A detailed description of the compressor is provided by Touyeras and Villain [13] and by Arnaud et al [14,15].…”

Section: Create Facility 21 Create Experimental Compressormentioning

confidence: 99%

Interaction of shrouded stator flow and main flow and its influence on performances of a three-stage high pressure compressor

Marty

Aupoix

2012

Proceedings of the Institution of Mechanical Engineers, Part A:

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The prediction of the complex flows within a turbomachinery remains a challenging issue for computational fluid dynamics (CFD). The real features of a turbomachinery must be taken into account in the simulation but they increase its complexity. One of these features is the leakage flow due to the axial gap between the fixed and rotating parts of the hub. This article focuses on this flow within the scope of a high-pressure compressor. The results are compared with experimental data obtained in the main flow path. The leakage flow is characterized by several vortices, especially near the hub and between the seal-teeth. It interacts with the main flow: the hub separation is quite wider while the casing one is reduced in comparison with the smooth case. In this article, the smooth case is related to the simulation without any shrouded stator cavity. The leakage flow influences strongly on compressor performances. Taking into account the leakage flow in the CFD improves the agreement between CFD and experimental values. Due to the vortex prediction, the influence of the turbulence modelling is also assessed. The explicit algebraic Reynolds stress model improves the flow prediction while the presently investigated differential Reynolds stress model predicts too wide hub corner separation which leads to high underestimation of compressor performances.

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Section: Create Facility 21 Create Experimental Compressormentioning

confidence: 99%

Interaction of shrouded stator flow and main flow and its influence on performances of a three-stage high pressure compressor

Marty

Aupoix

2012

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…For instance, rotor tip clearance variations and end-wall flows affect both efficiency [12] and aerodynamic stability [9,26]. Then, relative motions between fixed and rotating parts induce periodic unsteady flows that also modify overall performance, aerodynamic stability and the development of secondary flows [2,3]. The improvement of the compressor robustness and performance (for example by using control devices in the tip leakage region [24]) requires thus a better understanding of the flow physics that takes place in these systems.…”

Section: Introductionmentioning

confidence: 99%

Prediction of the unsteady turbulent flow in an axial compressor stage. Part 1: Comparison of unsteady RANS and LES with experiments

Gourdain

2015

Computers & Fluids

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a b s t r a c tA better understanding of turbulent unsteady flows is a necessary step towards a breakthrough in the design of modern gas turbine components. With the increase in computing power, LES emerges as a promising method to improve both knowledge of complex physics and reliability of flow solver predictions. However, there is still a lack of evidences in the literature that LES is applicable for turbomachinery at conditions relevant to industrial applications. In that context, the objective of the present work is to investigate the capability of LES to predict the turbulent flow in a stage of an axial compressor and compare the results with unsteady RANS data and experiments. The compressor operates at industrial relevant conditions, with Mach and Reynolds numbers equal to M ¼ 0:5 and Re ¼ 7 Â 10 5 , respectively. This paper presents the numerical method and a comparison of URANS and LES results to experimental data. A particular care is brought to estimate the results sensitivity to grid refinement (LES) and to turbulence and transition modelling (URANS). The comparison to experiments shows that LES better predicts time-dependent quantities than URANS, especially close to the casing. However, both URANS and LES fail to accurately estimate the compressor performance (efficiency and pressure ratio).

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“…Experimental and numerical techniques were used to understand the rotor blade tip flow phenomena in the space between blade tip and casing zone in axial flow compressor by L. Suder [8], the study showed tip clearance effect causes separation of flow from tip to hub which will be at 75% of rotor span at 100% speed. Flow field gets periodically modified because of unsteady flows due to the relative motions between static and rotating parts [9]. Most of the studies are limited to design condition.…”

Section: Manjunath S Dalbanjan and Niranjan Sarangimentioning

confidence: 99%

An Effect of Tip Clearance on Aero Performance in Axial Flow Compressors for Aero Gas Turbine Engines

Dalbanjan¹,

Tjprc²

2019

IJMPERD

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Gas turbine engines have dominated aviation industry, because they are highly efficient and reliable. Axial flow compressor is a critical part which plays a crucial role in efficiently working of an aero gas turbine engine. The entry and exit of the working fluid is in axial direction with respect to rotational axis in axial flow compressor. Higher mass flow swallowing capacityand higher efficiency for a small frontal area are unique features of axial flow compressors making an ideal option for the gas turbines used in jet engines., One of the major source of performance deterioration/enhancement in compressors is because of tip clearancebetween the rotor blade tip and casing. The tip clearance causes leakage of flow. The leaked flow interacts with the core flow and the wall boundary layer and control aerothermodynamics behavior of flow in the tip regions. This tip leakage flow also has an impact on efficiency and operating envelope of the compressor. In this work, a steady state analysis has been carried out to understand the influence of tip clearance on the aerodynamic performance of transonic single stage wide chord blade axial flow compressor stage through three dimensional viscous analysis using ANSYS CFX. The analysis was carried out for different tip clearance configuration varying from 0% to 1.2% of rotor tip axial chord. The characteristics plots like corrected massflow rate versus pressure ratio andcorrected massflow rate versus efficiency were plotted for various tip clearances at design speed. The generated database of tip clearance in this work will predictbeforehand the extent of deterioration due to manufacturing deviation of the components on aerodynamic performance prior to engine testing in the test bed.

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Experimental Investigation of the Rotor-Stator Interactions Within a High Speed, Multi-Stage, Axial Compressor: Part 1 — Experimental Facilities and Results

Cited by 9 publications

References 0 publications

Interaction of shrouded stator flow and main flow and its influence on performances of a three-stage high pressure compressor

Interaction of shrouded stator flow and main flow and its influence on performances of a three-stage high pressure compressor

Prediction of the unsteady turbulent flow in an axial compressor stage. Part 1: Comparison of unsteady RANS and LES with experiments

An Effect of Tip Clearance on Aero Performance in Axial Flow Compressors for Aero Gas Turbine Engines

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