Flow Field Simulations of a Gas Turbine Combustor

2002 ◽  
Vol 124 (3) ◽  
pp. 508-516 ◽  
Author(s):  
M. D. Barringer ◽  
O. T. Richard ◽  
J. P. Walter ◽  
S. M. Stitzel ◽  
K. A. Thole
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Large Scale ◽  
Guide Vane ◽  
Wall Region ◽  
Turbine Engine ◽  
Tunnel Section ◽  
Nozzle Guide ◽  
Nozzle Guide Vanes ◽  
Combustor Liner

The flow field exiting the combustor in a gas turbine engine is quite complex considering the presence of large dilution jets and complicated cooling schemes for the combustor liner. For the most part, however, there has been a disconnect between the combustor and turbine when simulating the flow field that enters the nozzle guide vanes. To determine the effects of a representative combustor flow field on the nozzle guide vane, a large-scale wind tunnel section has been developed to simulate the flow conditions of a prototypical combustor. This paper presents experimental results of a combustor simulation with no downstream turbine section as a baseline for comparison to the case with a turbine vane. Results indicate that the dilution jets generate turbulence levels of 15–18% at the exit of the combustor with a length scale that closely matches that of the dilution hole diameter. The total pressure exiting the combustor in the near-wall region neither resembles a turbulent boundary layer nor is it completely uniform putting both of these commonly made assumptions into question.

Flow Field Simulations of a Gas Turbine Combustor

2001 ◽  
Author(s):  
M. D. Barringer ◽  
O. T. Richard ◽  
J. P. Walter ◽  
S. M. Stitzel ◽  
K. A. Thole
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Large Scale ◽  
Guide Vane ◽  
Wall Region ◽  
Turbine Engine ◽  
Tunnel Section ◽  
Nozzle Guide ◽  
Nozzle Guide Vanes ◽  
Combustor Liner

The flow field exiting the combustor in a gas turbine engine is quite complex considering the presence of large dilution jets and complicated cooling schemes for the combustor liner. For the most part, however, there has been a disconnect between the combustor and turbine when simulating the flow field that enters the nozzle guide vanes. To determine the effects of a representative combustor flow field on the nozzle guide vane, a large-scale wind tunnel section has been developed to simulate the flow conditions of a prototypical combustor. This paper presents experimental results of a combustor simulation with no downstream turbine section as a baseline for comparison to the case with a turbine vane. Results indicate that the dilution jets generate turbulence levels of 15–18% at the exit of the combustor with a length scale that closely matches that of the dilution hole diameter. The total pressure exiting the combustor in the near wall region neither resembles a turbulent boundary layer nor is it completely uniform putting both of these commonly made assumptions into question.

Validation and Comparison of Strip Seal Designs for Gas Turbine Engine Nozzle Guide Vanes

2008 ◽  
Author(s):  
Arash Farahani ◽  
Peter Childs
Keyword(s):  
Gas Turbine ◽  
Guide Vane ◽  
Gas Turbine Engine ◽  
Experimental Comparison ◽  
Cfd Modelling ◽  
Guide Vanes ◽  
Turbine Engine ◽  
Seal Design ◽  
Nozzle Guide ◽  
Nozzle Guide Vanes

Strip seals are commonly used to prevent or limit leakage flows between nozzle guide vanes (NGV) and other gas turbine engine components that are assembled from individual segments. Leakage flow across, for example, a nozzle guide vane platform, leads to increased demands on the gas turbine engine internal flow system and a rise in specific fuel consumption (SFC). Careful attention to the flow characteristics of strip seals is therefore necessary. The very tight tolerances associated with strip seals provides a particular challenge to their characterisation. This paper reports the validation of CFD modelling for the case of a strip seal under very carefully controlled conditions. In addition, experimental comparison of three types of strip seal design, straight, arcuate, and cloth, is presented. These seals are typical of those used by competing manufacturers of gas turbine engines. The results show that the straight seal provides the best flow sealing performance for the controlled configuration tested, although each design has its specific merits for a particular application.

Failure Analysis of Heavy Industrial Gas Turbine Engine First Stage Nozzel Guide Vane

2012 ◽  
Vol 445 ◽  
pp. 1047-1052
Author(s):  
Alaaeldin H. Mustafa
Keyword(s):  
Failure Analysis ◽  
Gas Turbine ◽  
Guide Vane ◽  
Xrd Analysis ◽  
Optical Microscope ◽  
Guide Vanes ◽  
X Ray ◽  
Nozzle Guide ◽  
Industrial Gas Turbine ◽  
Nozzle Guide Vanes

Failure analysis investigation was conducted on 70 MW set of 1st stage turbine nozzle guide vanes (NGVs) of heavy industrial gas turbine. The failure was investigated using the light optical microscope (LOM), X-ray diffraction analysis (XRD) and energy dispersive X-ray spectroscopy (EDS) in an environmental scanning electron microscope (ESEM). The results of the analysis indicate that the NGVs which were made of Co base superalloy FSX-414 had been operated above the recommended operating hours under different fuel types in addition to inadequate repair process in previous repair removal. The XRD analysis of the fractured areas sample shows presence ofwhich might indicate the prolonged operation at high temperature. Keywords: cobalt-base; nozzle guide vanes, gas turbine.

Failure Analysis of Nozzle Guide Vane of a Low Pressure Turbine in an Aero Gas Turbine Engine

2014 ◽  
Vol 14 (5) ◽  
pp. 578-587 ◽  
Author(s):  
R. K. Mishra ◽  
Johney Thomas ◽  
K. Srinivasan ◽  
Vaishakhi Nandi ◽  
Raghavendra Bhat
Keyword(s):  
Failure Analysis ◽  
Gas Turbine ◽  
Guide Vane ◽  
Low Pressure ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Low Pressure Turbine ◽  
Nozzle Guide Vane ◽  
Nozzle Guide

scholarly journals Gas Turbine Testing on Naval Distillate Fuel

1971 ◽  
Author(s):  
J. S. Siemietkowski
Keyword(s):  
Gas Turbine ◽  
Diesel Fuel ◽  
Guide Vane ◽  
Engine Operation ◽  
Accelerated Corrosion ◽  
Turbine Engine ◽  
Base Materials ◽  
Nozzle Guide Vane ◽  
Nozzle Guide ◽  
Distillate Fuel

A Pratt & Whitney FT4A Marine Gas Turbine Engine rated at 22,600 hp, 3600 rpm was run at the Naval Ship Engineering Center, Philadelphia Division for 1000 hr. Fuel used was naval distillate having a vanadium level of 0.5 ppm. Basically there was no problem with engine operation on naval distillate when compared to diesel fuel. The smoke level was barely visible at high powers. Coalescent fuel filters are a problem due to their relatively short (100–130 hr) life. The corrosion rate was accelerated when compared to navy diesel fuel. The fuel parameter suspect is vanadium, however other parameters may be at fault. Additional efforts are required into definitely determining the cause of accelerated corrosion and also into optimizing nozzle guide vane and turbine blade base materials and coatings.

Study over thermal state of gas turbine engine metal-ceramic rotor blades and nozzle guide vanes under thermal shock and thermal-cyclic loading conditions

2004 ◽  
Vol 13 (2) ◽  
pp. 163-166
Author(s):  
A. V. Soudarev ◽  
A. A. Souryaninov ◽  
V. Ya. Podgorets ◽  
V. V. Grishaev ◽  
V.Yu Tikhoplav ◽  
...  
Keyword(s):  
Cyclic Loading ◽  
Thermal Shock ◽  
Gas Turbine ◽  
Thermal State ◽  
Rotor Blades ◽  
Guide Vanes ◽  
Turbine Engine ◽  
Metal Ceramic ◽  
Nozzle Guide ◽  
Nozzle Guide Vanes

Superposition Predictions of the Reduction of Hot Streaks by Coolant From a Film-Cooled Guide Vane

2009 ◽  
Vol 131 (4) ◽  
Author(s):  
Sean C. Jenkins ◽  
David G. Bogard
Keyword(s):  
Guide Vane ◽  
Operating Conditions ◽  
Measured Temperature ◽  
Turbine Engine ◽  
Temperature Distributions ◽  
Superposition Technique ◽  
Pass Through ◽  
Nozzle Guide ◽  
Hot Streak ◽  
Nozzle Guide Vanes

The turbine section of a gas turbine engine is subjected to hot gases flowing from the combustor that typically have high temperature regions known as “hot streaks.” These hot streaks pass through the nozzle guide vanes, either impacting the vanes or passing through the passages between vanes. Generally the vanes are highly film cooled, and the coolant from the vanes interacts with the hot streak resulting in a reduction of the hot streak temperature. In this study, predictions of the reduction of hot streaks were made using superposition of measured temperature distributions due to coolant injection and measured temperature distributions of hot streaks. These predictions were compared to the measured hot streak reduction to determine the accuracy of the superposition technique. Results showed that the superposition predictions generally underpredicted the reduction of the peak hot streak temperature, but were within at least 20% of the peak temperature value. The superposition technique was also found to be useful for determining the hot streak reduction for different hot streak locations, and different coolant and hot streak operating conditions.

Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization

2017 ◽  
Vol 0 (0) ◽  
Author(s):  
R K Mishra ◽  
Prashant Kumar ◽  
K Rajesh ◽  
C R Das ◽  
Ganapathi Sharma ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Guide Vane ◽  
Aluminide Coating ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Nozzle Guide Vane ◽  
Life Enhancement ◽  
Nozzle Guide ◽  
Metallurgical Evaluation ◽  
Operating Cycles

AbstractPack aluminization of high pressure turbine nozzle guide vane of an aero gas turbine engine has been carried out following a well defined systematic procedure. The process parameters are first optimized on dummy vanes and optimized process is followed for the actual vanes for evaluation and testing. Visual and binocular examination followed by metallurgical evaluation have been carried out to validate the process and to establish the adequacy and correctness of the coating. The coated vanes are then evaluated through engine level tests for performance and durability. The results of engine level tests and inspection post accelerated mission test cycles ensure that the vanes with aluminide coating can withstand severe engine operating cycles without any damage or failure which would otherwise would have happened without the coating. The condition of vanes post endurance test is also an indication of enhanced life of the vanes with coating.

scholarly journals Unsteady phenomena at the combustor-turbine interface

2021 ◽  
Vol 5 ◽  
pp. 202-215
Author(s):  
Faisal Shaikh ◽  
Budimir Rosic
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
High Speed ◽  
Guide Vane ◽  
Secondary Flows ◽  
Test Facility ◽  
Unsteady Heat Transfer ◽  
Guide Vanes ◽  
Nozzle Guide ◽  
Nozzle Guide Vanes

The combustor-turbine interface in a gas turbine is characterised by complex, highly unsteady flows. In a combined experimental and large eddy simulation (LES) study including realistic combustor geometry, the standard model of secondary flows in the nozzle guide vanes (NGV) is found to be oversimplified. A swirl core is created in the combustion chamber which convects into the first vane passages. Four main consequences of this are identified: variation in vane loading; unsteady heat transfer on vane surfaces; unsteadiness at the leading edge horseshoe vortex, and variation in the position of the passage vortex. These phenomena occur at relatively low frequencies, from 50–300 Hz. It seems likely that these unsteady phenomena result in non-optimal film cooling, and that by reducing unsteadiness designs with greater cooling efficiency could be achieved. Measurements were performed in a high speed test facility modelling a large industrial gas turbine with can combustors, including nozzle guide vanes and combustion chambers. Vane surfaces and endwalls of a nozzle guide vane were instrumented with 384 high speed thin film heat flux gauges, to measure unsteady heat transfer. The high resolution of measurements was such to allow direct visualisation in time of large scale turbulent structures over the endwalls and vane surfaces. A matching LES simulation was carried out in a domain matching experimental conditions including upstream swirl generators and transition duct. Data reduction allowed time-varying LES data to be recorded for several cycles of the unsteady phenomena observed. The combination of LES and experimental data allows physical explanation and visualisation of flow events.

A Calculation Tool of a Turbine Cooling Air Schedule for General Gas Turbine Simulation Algorithms

2011 ◽  
Vol 134 (4) ◽  
Author(s):  
Valerio Lallini ◽  
Jan Janikovic ◽  
Pericles Pilidis ◽  
Riti Singh ◽  
Panagiotis Laskaridis
Keyword(s):  
Gas Turbine ◽  
Operating Cost ◽  
Flight Path ◽  
Turbine Engine ◽  
Turbine Cooling ◽  
Cooling Flow ◽  
Conventional Cooling ◽  
Nozzle Guide ◽  
Nozzle Guide Vanes ◽  
Cooling Air

A tool to evaluate the turbine cooling air schedule during the flight path is presented. The method is suitable for complex gas turbine engine models where accurate calculation of thermodynamic parameters of a cooling flow used for studies such as specific fuel consumption (SFC), lifing, and operating cost analysis. The method is also applicable for land-based gas turbine engines where the flight path is replaced by load pattern. The method can be employed even if only a little information about the engine is known. The calculation method has been investigated on a model of a high bypass ratio turbofan for long haul application. Using it with an aircraft model and after comparing to conventional cooling air simulations, the reduction of SFC during the flight path has been observed. A comparison has been performed on engine manufacturer’s public domain data where the method shows comparable value of total cooling air needed. The tool returns similar results but estimates a higher proportion of cooling air for the high pressure turbine nozzle guide vanes (NGV) compared with Young and Wilcock’s method.

Sign in / Sign up

Export Citation Format

Share Document