Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
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R K Mishra
,
Prashant Kumar
Abstract
Pack 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.
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© 2017 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
Artikel in diesem Heft
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
