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.

scholarly journals Optimum Control of Variable Components in Aircraft Gas Turbine Engines Under Non-Stationary Flow Disturbances at the Inlet

1994 ◽  
Author(s):  
I. N. Egorov ◽  
G. V. Kreitinin
Keyword(s):  
Gas Turbine ◽  
Dynamic Control ◽  
Axial Flow ◽  
Stationary Flow ◽  
Turbine Engines ◽  
Stable Operation ◽  
Turbine Engine ◽  
Axial Flow Compressor ◽  
Flow Disturbances ◽  
Flow Compressor

A numerical method has been preposed to determine optimum laws to control gas turbine engine (CTE) variable components, including an independent control of blade rows in a multistage axial flow compressor under strong non-stationary flow disturbances at the inlet, optimum laws to control a turbofan under non-stationary thermal effects at the inlet have been obtained using mathematical models with various degree of filling in detail the flow in an engine flow path. There is shown a possibility to considerably increase a range of the CTE stable operation through the use of dynamic control of stator blades in a multistage axial flow compressor, also possibilities of practical use of optimum laws to control engine variable components in the system of preventing an unstable operation are being discussed.

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.

scholarly journals Causes for Turbomachinery Performance Deterioration

1988 ◽  
Author(s):  
W. Tabakoff
Keyword(s):  
Gas Turbine ◽  
Axial Flow ◽  
Leading Edge ◽  
Solid Particles ◽  
Two Stage ◽  
Axial Flow Compressor ◽  
Polluted Atmosphere ◽  
Performance Deterioration ◽  
Flow Compressor ◽  
Blunt Leading Edge

Turbines and compressors operating in polluted atmosphere with solid particles are subjected to performance deterioration. This paper presents an investigation carried out on two-stage gas turbine with blunt leading edge blades and on a single-stage axial flow compressor to study the effects of particulates and erosion on performance deterioration.

scholarly journals Developments Leading to an Axial Flow Compressor for a 25 MW Class High Efficiency Gas Turbine

1990 ◽  
Author(s):  
Y. Kashiwabara ◽  
Y. Katoh ◽  
H. Ishii ◽  
T. Hattori ◽  
Y. Matsuura ◽  
...  
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Mechanical Design ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Rotating Stall ◽  
Design Parameters ◽  
Axial Flow Compressor ◽  
Heavy Duty Gas Turbine ◽  
Flow Compressor

In this paper, the development leading to a 17-stage axial flow compressor (pressure ratio 14.7) for the 25 MW class heavy duty gas turbine H-25 is described. In the course of developing the H-25’s compressor, extensive measurements were carried out on models. Experimental results are compared with predicted values. Aerodynamic experiments covered the measurements of unsteady flows such as rotating stall and surge as well as the steady-state performance of the compressor. Based on the results of these tests, the aerodynamic and mechanical design parameters of the full scale H-25 compressor were finalized on the basis of two model compressors. Detailed measurements of the first unit of the H-25 gas turbine were carried out. Test results on the compressor are presented and show the achievement of the expected design targets.

scholarly journals Performance simulation of multi-stage axial-flow compressor of turbo-shaft engine with account for erosive wear nonlinearity of its blades

2020 ◽  
Vol 23 (5) ◽  
pp. 39-53
Author(s):  
V. A. Potapov ◽  
A. A. Sanko
Keyword(s):  
Gas Turbine ◽  
Axial Flow ◽  
Erosive Wear ◽  
Gas Turbine Engine ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Axial Flow Compressor ◽  
Multi Stage ◽  
Rotor Wing ◽  
Flow Compressor

The construction and useful practice of gas-turbine engine diagnosis systems depend largely on the availability of the engine mathematical models and its certain components in their structure. Utilization of multi-stage axial flow compressor performance with account for erosive wear of its parts during the operation fundamentally raises possibilities of such systems as erosive wear of flow channel, blade rings of impellers and vane rings of multi-stage compressor is a common cause of preschedule gas-turbine engine detaching from an aircraft. As evidenced by various contributions presented in the article, special emphasis on abrasive wear impact assessment on axial flow compressor performance is placed upon rotor-wing turbo-shaft engine due to their particular operating conditions. One of the main tasks in the process of mathematic simulation of an axial flow compressor blade ring is consideration of its wear type that again has a nonlinear distribution along the level of the blade. In addition, wear rate at entry and exit blade edges often have different principles. Detecting of these principles and their consideration when constructing the compressor mathematical model is a crucial task in diagnostic assessment and integrity monitoring of rotor-wing turbo-shaft engine in operation. The article represents a concept to an estimate nonlinear erosive wear effect of axial flow compressor blades on its performance based on the three-dimensional flow approach in the gas-air flow duct of compressor with a formulation of the blade rings. This approach renders possible to take into account the nonlinearity of the compressor blades wear during their operation. Through the example of the inlet compressor stage of a rotor-wing aircraft gas-turbine engine, the engine pump properties predictions with different kind of rotor blade wear have been 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.

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