Experimental Investigation of Jet Noise and Core Noise Using a Small Gas Turbine Engine

2002 ◽  
Author(s):  
Vincent Tesson ◽  
Michael Doty ◽  
Dennis McLaughlin
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Jet Noise ◽  
Gas Turbine Engine ◽  
Turbine Engine

Determination of Thermoacoustic Response in a Demonstrator Gas Turbine Engine

2000 ◽  
Author(s):  
C. A. Arana ◽  
B. Sekar ◽  
M. A. Mawid
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Analytical Model ◽  
Pressure Fluctuations ◽  
Gas Turbine Engine ◽  
Area Ratio ◽  
Fuel Injector ◽  
Acoustic Response ◽  
Turbine Engine ◽  
Discharge Area

This paper describes an analytical and experimental investigation to obtain the thermoacoustic response of a demonstrator gas turbine engine combustor. The combustor acoustic response for two different fuel injector design configurations was measured. It was found that the combustor maximum peak to peak pressure fluctuations were 0.6 psi to 2 psi for configuration A and B respectively. Based on the measured acoustic response, another experimental investigation was conducted to identify the design features in configuration B that caused the increase in the acoustic response. The data showed that by changing the fuel injector swirler’s vane to inner passage discharge area ratio, the engine acoustic response could be lowered to an acceptable level. A simplified analytical model based on the lumped-parameter approach was then developed to investigate the effect of geometrical changes upon the engine response. The analytical model predicted the fuel injector/swirlers acoustic response as a function of the swirlers inner passage discharge area ratio and frequency. The predictions were consistent with the experimental observations, in particular, it was predicted that as the area ratio was increased, the system reactance was decreased and as a result the system changed from a damping to an amplifying system.

Conditions for Scuffing Failure of Ground and Superfinished Steel Disks at High Sliding Speeds Using a Gas Turbine Engine Oil

1995 ◽  
Vol 117 (3) ◽  
pp. 482-489 ◽  
Author(s):  
M. J. Patching ◽  
C. C. Kweh ◽  
H. P. Evans ◽  
R. W. Snidle
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Surface Finish ◽  
Axial Direction ◽  
Gas Turbine Engine ◽  
Hardened Steel ◽  
Engine Oil ◽  
Turbine Engine ◽  
Involute Gears ◽  
Scuffing Failure

This paper describes the results of an experimental investigation to compare the scuffing performance of conventionally ground and superfinished hardened steel disks operating at sliding speeds of up to 26 m/s and lubricated with a gas turbine engine oil at a temperature of 100° C. The ground disks were finished in the axial direction to simulate the orientation of surface finish found on involute gears. Superfinishing was found to give a significant increase in the load at which scuffing occurred. Frictional traction was also measured in the experiments and was found to be significantly lower for the superfinished disks in the loading stages preceding scuffing failure.

Experimental Investigation of an Inert Gas Generator for Fire Suppressing

2001 ◽  
Author(s):  
SooYong Kim ◽  
A. Slitenko
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Mass Flow Rate ◽  
Oxygen Content ◽  
Flow Rate ◽  
Gas Turbine Engine ◽  
Inert Gas ◽  
Gas Generator ◽  
Turbine Engine ◽  
Exit Nozzle

Present study deals with experimental and theoretical performance analysis of an inert gas generator(IGG) which can be used as an effective mean to suppress the fire. The system consists of a gas turbine engine and afterburning system with injection of water, exit nozzle to produce the inert gas. It is generally known that the degree of oxygen content in the product of combustion depends on both inlet and outlet temperature of a combustor. Less the oxygen content in the combustion product higher will be the effectiveness of fire suppression. Injection of water brings additional advantages of suffocating and cooling effects which are both indespensable factors for fire suppressing. The special test rig was manufactured and experimental investigation of IGG system has been carried out. The automatic control system ensured stable operation of gas turbine engine and afterburner, water injection, fuel control and others. During the investigation the main parameters of gas turbine engine and auxiliarly systems were measured: gas temperature and pressure at gas turbine and afterburner exit, fuel flow rate, water mass flow rate, inlet air temperature, water temperature in the cooling chamber, mass flow rate, temperature and velocity of exhaust gas-steam mixture in the exit nozzle, oxygen content in the exit jet. The experimental investigation shows that developed IGG system can work very well for indoor fires but need some modifications in application to outdoor fire suppressing.

Determination of Thermoacoustic Response in a Demonstrator Gas Turbine Engine

2000 ◽  
Vol 124 (1) ◽  
pp. 46-57 ◽  
Author(s):  
C. A. Arana ◽  
B. Sekar ◽  
M. A. Mawid ◽  
C. B. Graves
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Analytical Model ◽  
Pressure Fluctuations ◽  
Gas Turbine Engine ◽  
Area Ratio ◽  
Fuel Injector ◽  
Acoustic Response ◽  
Turbine Engine ◽  
Discharge Area

This paper describes an analytical and experimental investigation to obtain the thermoacoustic response of a demonstrator gas turbine engine combustor. The combustor acoustic response for two different fuel injector design configurations was measured. It was found that the combustor maximum peak to peak pressure fluctuations were 0.6 psi to 2 psi for configuration A and B, respectively. Based on the measured acoustic response, another experimental investigation was conducted to identify the design features in configuration B that caused the increase in the acoustic response. The data showed that by changing the fuel injector swirler’s vane to inner passage discharge area ratio, the engine acoustic response could be lowered to an acceptable level. A simplified analytical model based on the lumped-parameter approach was then developed to investigate the effect of geometrical changes upon the engine response. The analytical model predicted the fuel injector/swirlers acoustic response as a function of the swirlers inner passage discharge area ratio and frequency. The predictions were consistent with the experimental observations, in particular, it was predicted that as the area ratio was increased, the system reactance was decreased and as a result the system changed from a damping to an amplifying system.

Effect of jet noise reduction on gas turbine engine efficiency

2012 ◽  
Vol 227 (9) ◽  
pp. 1441-1455 ◽  
Author(s):  
Georgios Doulgeris ◽  
Theodosios Korakianitis ◽  
Eldad J Avital ◽  
Pericles Pilidis ◽  
Panos Laskaridis
Keyword(s):  
Noise Reduction ◽  
Gas Turbine ◽  
Jet Noise ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Efficiency
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