FORECASTING NONUNIFORMITY OF GAS TEMPERATURE FIELD AT THE GAS TURBINE ENGINE COMBUSTOR OUTLET IN THE CASE OF INDEFINITENESS OF INITIAL CONDITIONS OF ATOMIZED FUEL SUPPLY

2016 ◽  
Vol 20 (1) ◽  
pp. 23-32
Author(s):  
Omair Alhatim
Keyword(s):  
Temperature Field ◽  
Gas Turbine ◽  
Initial Conditions ◽  
Gas Turbine Engine ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Fuel Supply

scholarly journals A Parametric Starting Study of an Axial-Centrifugal Gas Turbine Engine Using a One-Dimensional Dynamic Engine Model and Comparisons to Experimental Results: Part 1 — Model Development and Facility Description

1998 ◽  
Author(s):  
A. Karl Owen ◽  
Anne Daugherty ◽  
Doug Garrard ◽  
Howard C. Reynolds ◽  
Richard D. Wright
Keyword(s):  
Gas Turbine ◽  
Initial Conditions ◽  
Model Development ◽  
Ground Level ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Gas Generator ◽  
Turbine Engine ◽  
One Dimensional ◽  
Engine Model

A generic one-dimensional gas turbine engine model, developed at the Arnold Engineering Development Center, has been configured to represent the gas generator of a General Electric axial-centrifugal gas turbine engine in the six kg/sec airflow class. The model was calibrated against experimental test results for a variety of initial conditions to insure that the model accurately represented the engine over the range of test conditions of interest. These conditions included both assisted (with a starter motor) and unassisted (altitude windmill) starts. The model was then exercised to study a variety of engine configuration modifications designed to improve its starting characteristics and thus quantify potential starting improvements for the next generation of gas turbine engines. This paper discusses the model development and describes the test facilities used to obtain the calibration data. The test matrix for the ground level testing is also presented. A companion paper presents the model calibration results and the results of the trade-off study.

Gas turbine engine gas temperature measurement by acoustic multivibrators with fast Fourier transform

2021 ◽  
Author(s):  
Zh. A. Sukhinets ◽  
A. I. Gulin ◽  
A. L. Galiev ◽  
Sh. R. Akhmetov
Keyword(s):  
Fourier Transform ◽  
Fast Fourier Transform ◽  
Temperature Measurement ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Gas Temperature ◽  
Turbine Engine

scholarly journals Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

2018 ◽  
Vol 2018 ◽  
pp. 1-12 ◽  
Author(s):  
Mustagime Tülin Yildirim ◽  
Bülent Kurt
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Gas Turbine Engine ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Fuel Flow ◽  
The Status ◽  
Performance Deterioration ◽  
Artificial Neural Network Ann

Modern condition monitoring-based methods are used to reduce maintenance costs, increase aircraft safety, and reduce fuel consumption. In the literature, parameters such as engine fan speeds, vibration, oil pressure, oil temperature, exhaust gas temperature (EGT), and fuel flow are used to determine performance deterioration in gas turbine engines. In this study, a new model was developed to get information about the gas turbine engine’s condition. For this model, multiple regression analysis was carried out to determine the effect of the flight parameters on the EGT parameter and the artificial neural network (ANN) method was used in the identification of EGT parameter. At the end of the study, a network that predicts the EGT parameter with the smallest margin of error has been developed. An interface for instant monitoring of the status of the aircraft engine has been designed in MATLAB Simulink. Any performance degradation that may occur in the aircraft’s gas turbine engine can be easily detected graphically or by the engine performance deterioration value. Also, it has been indicated that it could be a new indicator that informs the pilots in the event of a fault in the sensor of the EGT parameter that they monitor while flying.

scholarly journals Development of the AGT101 Regenerator Seals

1987 ◽  
Author(s):  
C. A. Fucinari ◽  
J. K. Vallance ◽  
C. J. Rahnke
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Dynamic Test ◽  
Development Program ◽  
Analytical Techniques ◽  
Gas Turbine Engine ◽  
Inlet Temperature ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Seal Design

The design and development of the regenerator seals used in the AGT101 gas turbine engine are described in this paper. The all ceramic AGT101 gas turbine engine was designed for 100 hp at 5:1 pressure ratio with 2500F (1371C) turbine inlet temperature. Six distinct phases of seal design were investigated experimentally and analytically to develop the final design. Static and dynamic test rig results obtained during the seal development program are presented. In addition, analytical techniques are described. The program objectives of reduced seal leakage, without additional diaphragm cooling, to 3.6% of total engine airflow and higher seal operating temperature resulting from the 2000F (1093C) inlet exhaust gas temperature were met.

A Parametric Starting Study of an Axial-Centrifugal Gas Turbine Engine Using a One-Dimensional Dynamic Engine Model and Comparisons to Experimental Results: Part II—Simulation Calibration and Trade-Off Study

1999 ◽  
Vol 121 (3) ◽  
pp. 384-393 ◽  
Author(s):  
A. K. Owen ◽  
A. Daugherty ◽  
D. Garrard ◽  
H. C. Reynolds ◽  
R. D. Wright
Keyword(s):  
Gas Turbine ◽  
Initial Conditions ◽  
Model Development ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Gas Generator ◽  
Trade Off ◽  
Turbine Engine ◽  
One Dimensional ◽  
Engine Model

A generic one-dimensional gas turbine engine model, developed at the Arnold Engineering Development Center, has been configured to represent the gas generator of a General Electric axial-centrifugal gas turbine engine in the six-kg/sec airflow class. The model was calibrated against experimental test results for a variety of initial conditions to insure that the model accurately represented the engine over the range of test conditions of interest. These conditions included both assisted (with a starter motor) and unassisted (altitude windmill) starts. The model was then exercised to study a variety of engine configuration modifications designed to improve its starting characteristics and thus quantify potential starting improvements for the next generation of gas turbine engines. This paper presents the model calibration results and the results of the trade-off study. A companion paper discusses the model development and describes the test facilities used to obtain the calibration data.

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.

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