Wavelet analysis of air-jet injection stall control effects in an axi-centrifugal gas turbine engine

1997 ◽  
Author(s):  
Dzu Le ◽  
Albert Owen ◽  
Donald Simon ◽  
Dzu Le ◽  
Albert Owen ◽  
...  
Keyword(s):  
Wavelet Analysis ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Jet Injection ◽  
Turbine Engine ◽  
Air Jet ◽  
Stall Control

INVESTIGATION OF EXHAUSTING PHENOMENA OF GAS TURBINE ENGINE ON THE BASIS OF WAVELET ANALYSIS

2018 ◽  
pp. 24-33
Author(s):  
N. V. Tkacheshak ◽  
М. І. Horbiichuk
Keyword(s):  
Wavelet Analysis ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Air Pressure ◽  
Discrete Wavelet ◽  
Wavelet Coefficients ◽  
Selection Scheme ◽  
Turbine Engine ◽  
Pressure Signal ◽  
Advantages And Disadvantages

The method for research of a gas turbine engine (GTE) surging phenomena based on wavelet analysis was developed. GTE DG-90 was chosen for research. A wavelet decomposition of the air pressure signal was carried out using a high pressure compressor and Dobeski, Symlet, Coffle and Meyer's discrete wavelet. The advantages and disadvantages of filtering properties of these wavelets were graphically represented in the form of amplitude-frequency characteristics. Based on the results obtained, a wavelet transform parameter selection scheme based on the analysis of the frequency response of wavelet filters was constructed, and the optimum sampling time of the wavelet filtering of the investigated signal was calculated for determination of the propagation and rotational breakdown in the GTE turbocompressor. According to this scheme, among the wavelets of Dobeski, Simlet, Koefleta, and Meyer's discrete wavelet, for studying the air pressure signal at the compressor during bursting processes, the first were selected by the Dobeches and Symmetes wavelets of the 2nd order according to their filtration rate. Considering high speed and characteristics of the description of the occurrence of excite phenomena by means of a fast Fourier transform to the distribution of the wavelet coefficients of the air pressure signal by turbocompressor, for the diagnosis of unstable flows occurring in the gas path of the gas turbine trajectory (surging and rotary breakdown), the Dobeski wavelet was selected 2nd order. At the same time, to monitor the wavelet coefficients behavior, the detail of the investigated signal is necessary at the 7th level of decomposition. Thus, the obtained results allow to carry out further analysis of breakdown processes using low-order wavelets.

Multiple Jet Correlations for Gas Turbine Engine Combustor Design

1976 ◽  
Vol 98 (2) ◽  
pp. 265-272 ◽  
Author(s):  
G. B. Cox
Keyword(s):  
Temperature Field ◽  
Gas Turbine ◽  
Correlation Method ◽  
Gas Turbine Engine ◽  
Measured Data ◽  
Jet Injection ◽  
Turbine Engine ◽  
Single Row ◽  
Flow Variables ◽  
Correlation Procedure

A correlation method has been developed for predicting the temperature field produced by a single row of closely-spaced jets penetrating into a hot confined crossflow. The correlation procedure predicts the temperature field as a function of the distance downstream of the jet injection plane and pertinent geometric and flow variables. Predicted results are compared with measured data. The tests are selected to represent combinations of geometries or flow variables which give strong verification of the correlations and which are pertinent to gas turbine engine combustor design.

scholarly journals An Air Jet Distortion Generation System

2014 ◽  
Vol 2014 ◽  
pp. 1-17
Author(s):  
M. Sivapragasam ◽  
S. Ramamurthy ◽  
M. D. Deshpande ◽  
P. White
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Total Pressure ◽  
Gas Turbine Engine ◽  
Test Facility ◽  
Generation System ◽  
Turbine Engine ◽  
Air Jet ◽  
Engine Testing ◽  
Distortion Parameters

An air jet distortion generation system is developed to simulate the distorted flow field ahead of gas turbine engines in ground test facility. The flow field of a system of four jets arranged circumferentially and issuing into a confined counterflow was studied experimentally and numerically. The total pressure distortion parameters were evaluated at the Aerodynamic Interface Plane (AIP) for several values of mass flow ratios. Since the total pressure loss distribution at theAIPis characteristically “V” shaped, the number of jets was increased to obtain total pressure distributions as required for gas turbine engine testing. With this understanding, a methodology has been developed to generate a target total pressure distortion pattern at theAIP. Turbulent flow computations are used to iteratively progress towards the target distribution. This methodology was demonstrated for a distortion flow pattern typical of use in gas turbine engine testing using twenty jets, which is a smaller number than reported in the literature. The procedure converges with a root-mean-square error of 3.836% and is able to reproduce the target pattern and other distortion parameters.

Flexible manufacturing in repair of gas turbine engine components

1992 ◽  
Author(s):  
KIRK D ◽  
ANDREW VAVRECK ◽  
ERIC LITTLE ◽  
LESLIE JOHNSON ◽  
BRETT SAYLOR
Keyword(s):  
Gas Turbine ◽  
Flexible Manufacturing ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Components

Fracture of a Compressor Stator Blade in a Gas Turbine Engine

2013 ◽  
Vol 50 (1) ◽  
pp. 43-49
Author(s):  
A. Neidel ◽  
B. Matijasevic-Lux
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Stator Blade
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