Investigation of Instability Inception in a High-Speed Axial-Flow Compressor Using Chaos Theory

2002 ◽  
Author(s):  
Tsuguji Nakano ◽  
Hidekazu Kodama
Keyword(s):  
Chaos Theory ◽  
High Speed ◽  
Axial Flow ◽  
Axial Flow Compressor ◽  
Flow Compressor

Stall cell blockage in a high-speed multistage axial-flow compressor

1990 ◽  
Author(s):  
STEVEN GORRELL ◽  
WILLIAM COPENHAVER ◽  
WALTER O'BRIEN
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Axial Flow Compressor ◽  
Flow Compressor

scholarly journals The Numerical Simulation of a High-Speed Axial Flow Compressor

1991 ◽  
Author(s):  
Richard A. Mulac ◽  
John J. Adamczyk
Keyword(s):  
Numerical Simulation ◽  
Data Storage ◽  
High Speed ◽  
Axial Flow ◽  
Equation System ◽  
Axial Flow Compressor ◽  
Code Performance ◽  
Recent Developments ◽  
Multistage Compressors ◽  
Flow Compressor

The advancement of high-speed axial flow multistage compressors is impeded by a lack of detailed flow field information. Recent developments in compressor flow modeling and numerical simulation have the potential to provide needed information in a timely manner. This paper, which consists of two parts, will explore this topic. The first part will address the development of a computer program to solve the viscous form of the average-passage equation system for multistage turbomachinery. Programming issues such as in-core versus out-of-core data storage and CPU utilization (parallelization, vectorization, and chaining) will be addressed. Code performance will be evaluated through the simulation of the first four stages of a five stage, high-speed, axial flow compressor on a CRAY Y-MP8/8128 computer. The second part will address the flow physics which can be obtained from the numerical simulation. In particular, an examination of the endwall flow structure will be made, and its impact on blockage distribution assessed.

Compound Piston-and-Turbine Engines

1959 ◽  
Vol 81 (3) ◽  
pp. 259-264 ◽  
Author(s):  
A. L. London
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Axial Flow ◽  
Turbine Engines ◽  
Exhaust Gas ◽  
Prime Mover ◽  
Axial Flow Compressor ◽  
Flow Compressor

The prime-mover combination of piston-and-cylinder components with a high-speed exhaust-gas turbine and, in some cases, a centrifugal or axial-flow compressor has assumed a variety of forms. Progress in the development of some of the more notable members of this family of compound engines is presented.

Effect of Turbulence Model on the Prediction of Performance and Span-Wise Mixing in High-Speed Highly-Loaded Multi-Stage Axial-Flow Compressor

2019 ◽  
Author(s):  
Takashi Goto ◽  
Tetsuya Oshio ◽  
Naoki Tani ◽  
Mizuho Aotsuka ◽  
Guillaume Pallot ◽  
...  
Keyword(s):  
Flow Field ◽  
Turbulence Model ◽  
High Speed ◽  
Axial Flow ◽  
Weno Scheme ◽  
Axial Flow Compressor ◽  
Multi Stage ◽  
Radial Profiles ◽  
Flow Compressor ◽  
Highly Loaded

Abstract Despite significant advancements in computational power and various numerical modeling in past decades, flow simulation of a multi-stage axial-flow compressor is still one of the most active areas of research, for it is the critical component in engine performance and operability, and there are so many elements that need to be looked into to predicting correct matching of the stages and accurate flow distribution inside the machine. Modeling unsteadiness, both deterministic and random types, and real geometries are among the most important features to be considered in such prediction. The authors have conducted in their previous studies a series of unsteady RANS (URANS) simulations of a 6.5-stage high-speed highly-loaded axial-flow compressor, and explored many unsteady effects as well as effects of real geometries such as Variable Stator Vane (VSV) clearance and inter-stage seal leakage flow on the compressor performance. However, all the analyses failed to predict correct stage matching, total pressure and temperature radial profiles, or mass-flow with adequate accuracies. In the present study, an Improved Delayed Detached Eddy Simulation (IDDES) with SST k-omega model is applied to the simulation of the same compressor configuration at aerodynamic design point. Fifth-order WENO scheme is employed for improved spatial accuracy to suppress significant increase in mesh size. Total number of mesh points are over 400 million for 1/10th sector model. Computations are ensemble averaged for 20 sector passage. Computed overall performance and flow field are compared with the compressor rig test data. The predictions of inter-stage total temperature radial profiles are noticeably improved over the URANS with the same mesh, discretization scheme and eddy turbulence model. Good comparison with the rig data indicates the current simulation is properly capturing the span-wise mixing phenomena. Unsteady flow field are compared between IDDES and URANS to locate the cause for the enhanced mixing. It is shown that components of Reynolds stress responsible for radial diffusion and anisotropic features are intensified in the tip leakage vortex at the rotor exit for the IDDES.

Research on High Speed Axial Flow Compressor

1961 ◽  
Vol 64 (511) ◽  
pp. 1140-1148
Author(s):  
Masakatsu MATSUKI ◽  
Toshio MIYACHI
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Axial Flow Compressor ◽  
Flow Compressor

The Influence of Shrouded Stator Cavity Flows on the Aerodynamic Performance of a High-Speed Multistage Axial-Flow Compressor

2011 ◽  
Author(s):  
Dai Kato ◽  
Mai Yamagami ◽  
Naoki Tsuchiya ◽  
Hidekazu Kodama
Keyword(s):  
High Speed ◽  
Three Dimensional ◽  
Axial Flow ◽  
Main Flow ◽  
Navier Stokes ◽  
Cavity Flows ◽  
Axial Flow Compressor ◽  
First Case ◽  
Flow Compressor ◽  
Unsteady Effects

This paper investigates numerically the effects of shrouded stator seal cavity flows on a high-speed, six-stage, advanced axial-flow compressor performance. Two cases of fully three-dimensional unsteady Reynolds-averaged Navier-Stokes simulations are performed. The first case includes only the main flow path without cavities, while the second case takes into account the effect of cavities by fully meshing and solving the seal cavity flows under each of the stator vanes. Both simulations included rotor blade tip clearances. The latter case showed 1.7 point degradation in efficiency from the first case. Contributors to the overall performance degradation, such as windage heating, mixing loss due to seal leakage flow with the main flow, and additional loss of the rotors and stators due to alteration in velocity triangles, are identified by comparing the two simulation results. Compared to theoretical or semi-empirical leakage and windage models, higher loss production and temperature rise are found especially in mid to rear stages. Unsteady effects for such differences are discussed.

Unsteady Total Pressure Field Downstream of an Embedded Stator in a Multistage Axial Flow Compressor

1997 ◽  
Vol 119 (4) ◽  
pp. 985-994 ◽  
Author(s):  
N. Suryavamshi ◽  
B. Lakshminarayana ◽  
J. Prato ◽  
J. R. Fagan
Keyword(s):  
Total Pressure ◽  
High Speed ◽  
Pressure Field ◽  
Axial Flow ◽  
Temporal Variations ◽  
Pressure Probe ◽  
Peak Efficiency ◽  
Axial Flow Compressor ◽  
Multistage Compressors ◽  
Flow Compressor

The results from measurements of the unsteady total pressure field downstream of an embedded stage of a three stage axial flow compressor are presented in this paper. The measurements include area traverses of a high response kulite total pressure probe and a pneumatic five hole probe downstream of stator 2 at the peak efficiency operating point for the compressor. These data indicate that both the shaft-resolved and unresolved fluctuations contribute to the unsteadiness of the total pressure field in multistage compressors. Specifically, regions associated with high levels of unsteadiness and, consequently, high levels of mixing including both the hub and casing end walls and the airfoil wakes have significant levels of shaft resolved and unresolved unsteadiness. Temporal variations of stator exit flow are influenced by both shaft resolved and unresolved unsteadiness distributions. The limitations of state-of-the-art instrumentation for making measurements in moderate and high speed turbomachinery and the decomposition used to analyze these data are also discussed.

scholarly journals Effect of the Rear Stage Casing Treatment on the Overall Performance of a Multistage Axial-Flow Compressor

1982 ◽  
Author(s):  
Yao-Lin Gao ◽  
Ke-Ming Li
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Rotor Blades ◽  
Stall Margin ◽  
Casing Treatment ◽  
Axial Flow Compressor ◽  
Surge Margin ◽  
Engine Compressor ◽  
Overall Performance ◽  
Flow Compressor

This paper discusses the effect of tip treatment in the rear stages of a compressor on the high speed stall margin and efficiency. A nine stage engine compressor was tested in a rig with and without casing treatment on the tip sections of the last three rotors. Another series of tests were conducted on a modified compressor with twisted rotor blades in the rear stages. For both compressors, tip treatment improved high speed surge margin. The first compressor encountered no loss of efficiency with the addition of tip treatment, but the second compressor suffered a loss of efficiency.

Experimental Investigation of Rotating Stall in a Mismatched Three-Stage Axial Flow Compressor

1989 ◽  
Vol 111 (4) ◽  
pp. 418-425 ◽  
Author(s):  
G. L. Giannissis ◽  
A. B. McKenzie ◽  
R. L. Elder
Keyword(s):  
High Speed ◽  
Measurement Techniques ◽  
Axial Flow ◽  
Fast Response ◽  
Rotating Stall ◽  
Response Measurement ◽  
Stall Inception ◽  
Axial Flow Compressor ◽  
Multistage Compressors ◽  
Flow Compressor

This paper reports on an examination of rotating stall in a low-speed three-stage axial flow compressor operating with various degrees of stage mismatch. The objective of this study was to simulate the mismatching that occurs in high-speed multistage compressors when operating near surge. The study of the stall zones involved the use of fast response measurement techniques. The study clearly shows how stages can operate in an axisymmetric fashion even when heavily stalled, since rotating stall inception requires the stall of more than one stage. The study also compares conditions required for full-span and part-span stall and suggests that the part-span stall structure is more relevant to high-speed multistage compressors.

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