Shape memory alloy adaptive control of gas turbine engine compressor blade clearance

1998 ◽  
Author(s):  
L. Schetky ◽  
Charles Lei ◽  
Bruce Steinetz ◽  
James Sublett
Keyword(s):  
Adaptive Control ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Compressor Blade ◽  
Turbine Engine ◽  
Blade Clearance ◽  
Engine Compressor

scholarly journals Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades

2019 ◽  
Vol 18 (1) ◽  
pp. 109-117
Author(s):  
M. B. Sazonov ◽  
L. V. Solovatskaya
Keyword(s):  
Residual Stress ◽  
Stressed State ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Graphical Analysis ◽  
Compressor Blade ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Compressive Stresses ◽  
Engine Compressor

Different types of final strengthening treatment of gas turbine engine (GTD) compressor blades are considered. The influence of each type of treatment on the formation of roughness of the surface with favorable microrelief, as well as on the level and depth of distribution of residual compressive stresses in the compressor blade airfoil is analyzed. The causes of blade fatigue failure are described and methods of controlling this kind of failure are presented. The results of testing special specimens made of VT9 titanic alloy are presented to establish the influence of final strengthening treatment modes on the compressor blade resistance to fatigue stress. The results of testing residual stress distribution along the thickness of compressor blade airfoil are presented. A method of improving dynamic strengthening of specimens due to the protection of compressor blade edges is discussed. The results of semi-graphical analysis of the stressed state of low-pressure and medium-pressure compressor blades made of VT9 alloy are presented. They take into account residual stresses, as well as operating load stresses in the process of operation. We show that it is possible to increase the limit of the blade endurance due to the optimization of residual stress diagrams by improving the final strengthening technology with the use of dust blasting.

Compensation of Intake Induced Flow Non-Uniformities With Compressor Blade Lean Angle Changes

2009 ◽  
Author(s):  
Ioannis Templalexis ◽  
Vassilios Pachidis ◽  
Petros Kotsiopoulos
Keyword(s):  
Gas Turbine ◽  
Flow Simulation ◽  
Gas Turbine Engine ◽  
Compressor Blade ◽  
Design Stage ◽  
Computational Time ◽  
Turbine Engine ◽  
Lean Angle ◽  
Compressor Performance ◽  
Induced Flow

The compression system has traditionally drawn most of the attention concerning the gas turbine engine performance assessment and design procedure. It is the most vulnerable component to flow fluctuations within a gas turbine engine. In particular this study focuses on performance deviations, between an installed and an uninstalled compressor. Test results acquired from a test bed installation will differ from these recorded when the compressor operates as an integral part of the engine. The upstream duct, whether an intake or an interstage duct, will affect the flow field pattern ingested into the compressor. The case studies presented into this work aim to mostly qualify the effect of boundary layer growth along the upstream duct walls, upon compressor performance. Additionally, compressor performance response on blade lean angle variation is being addressed, with the aim of acquiring an understanding as to how compressor blade lean angle changes interact with intake induced flow non uniformities. Such studies are usually conducted during the preliminary design stage, before the compressor is built. Consequently, experimental performance investigation is excluded at this stage of development. Computer aided simulation techniques are between the few if not the only option for compressor performance prediction. Given the fact that many such design parameters need to be assessed under the time pressure exerted by the tight compressor development program, the compressor flow simulation technique used needs to provide reliable results while consuming the least possible computational time. Such a low computational time compressor flow simulation method, among others, is the two dimensional (2D) streamline curvature (SLC) method, being applied within the frame of reference of the current study. The paper is introduced by a brief discussion on SLC method that was proposed more than 50 years ago. Then a reference is made to the Radial Equilibrium Equation (REE) which is the mathematical basis of the code, commenting on the assumptions that were undertaken. Subsequently the influence of the intake presence on the compressor inlet radial flow distribution is being addressed, with the aim of adjusting compressor blade inlet lean angle, in order to minimize compressor performance deterioration. Finally the paper is concluded with a discussion of the results.

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