Rig and Engine Testing of Melt Infiltrated Ceramic Composites for Combustor and Shroud Applications

2002 ◽  
Vol 124 (3) ◽  
pp. 459-464 ◽  
Author(s):  
G. S. Corman ◽  
A. J. Dean ◽  
S. Brabetz ◽  
M. K. Brun ◽  
K. L. Luthra ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Ceramic Composites ◽  
Gas Turbine Engine ◽  
Matrix Composites ◽  
Turbine Engine ◽  
Sic Fiber ◽  
Silicon Melt ◽  
Melt Infiltration ◽  
Engine Testing ◽  
Observed Damage

General Electric has developed SiC fiber-reinforced SiC-Si matrix composites produced by silicon melt infiltration for use in gas turbine engine applications. High temperature, high-pressure combustion rig testing, and engine testing has been performed on combustor liners and turbine shrouds made from such MI composites. Frame 5 sized combustor liners were rig tested under lean head end diffusion flame conditions for 150 hours, including 20 thermal trip cycles, with no observed damage to the ceramic liners. Similarly, 46-cm diameter, single-piece turbine shroud rings were fabricated and tested in a GE-2 gas turbine engine. The fabrication and testing of both components are described.

Rig and Engine Testing of Melt Infiltrated Ceramic Composites for Combustor and Shroud Applications

2000 ◽  
Author(s):  
Gregory S. Corman ◽  
Anthony J. Dean ◽  
Stephen Brabetz ◽  
Milivoj K. Brun ◽  
Krishan L. Luthra ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Ceramic Composites ◽  
Gas Turbine Engine ◽  
Matrix Composites ◽  
Turbine Engine ◽  
Sic Fiber ◽  
Silicon Melt ◽  
Melt Infiltration ◽  
Engine Testing ◽  
Observed Damage

GE has developed SiC fiber reinforced SiC-Si matrix composites produced by silicon melt infiltration (MI) for use in gas turbine engine applications. High temperature, high pressure combustion rig testing and engine testing has been performed on combustor liners and turbine shrouds made from such MI composites. Frame 5 sized combustor liners were rig tested under LHE diffusion flame conditions for 150 hours, including 20 thermal trip cycles, with no observed damage to the ceramic liners. Similarly, 46 cm diameter, single piece turbine shroud rings were fabricated and tested in a PGT-2 gas turbine engine. The fabrication and testing of both components are described.

SiC Fiber Reinforced SiC-Si Matrix Composites Prepared by Melt Infiltration (MI) for Gas Turbine Engine Applications

1999 ◽  
Author(s):  
Gregory S. Corman ◽  
Milivoj K. Brun ◽  
Krishan L. Luthra
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Matrix Cracking ◽  
Matrix Composites ◽  
Fiber Reinforced ◽  
Turbine Engine ◽  
Sic Fiber ◽  
Silicon Melt ◽  
Melt Infiltration ◽  
Near Net Shape

General Electric (GE) has developed silicon carbide fiber reinforced SiC-Si matrix composites by silicon melt infiltration (MI) for use in gas turbine engine applications. This paper focuses on a process based on tow prepreging and lamination of unidirectional tapes. Silicon melt infiltration yields a fully dense, near net shape composite with a relatively high thermal conductivity, actually higher than many superalloys at temperatures up to 800°C, and a high proportional limit, or matrix cracking stress. Room and elevated temperature mechanical properties of the composite are presented. Following exposure to various simulated turbine environments this material shows relatively good retention of strength and toughness. The fabrication of turbine shroud and combustor liner components for high pressure combustion rig testing is also described.

Rig and Gas Turbine Engine Testing of MI-CMC Combustor and Shroud Components

2001 ◽  
Author(s):  
Gregory Corman ◽  
Anthony Dean ◽  
Stephen Brabetz ◽  
Keith McManus ◽  
Milivoj Brun ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Ceramic Matrix Composites ◽  
Gas Turbine Engine ◽  
Matrix Composites ◽  
Turbine Engine ◽  
Single Piece ◽  
Engine Testing ◽  
Engine Components ◽  
Industrial Gas Turbine

GE is continuing work on the development of Melt-Infiltrated Ceramic Matrix Composites (MI-CMC) for use in industrial gas turbine engine components. Long-term environmental degradation of test samples under realistic engine conditions is being determined using a unique high-pressure combustion rig apparatus. Rig testing is also being used to evaluate an F-class 1st stage shroud system incorporating an MI-CMC inner shroud component. While large, advanced engines, such as the F and H classes, offer the greatest benefits for using MI-CMC components, initial engine tests have been done using a GE-2 (2MW) machine to reduce costs and risk. Long term (1000 hours) engine testing results for single piece GE-2 shrouds are also described.

Simple Instrumentation Rake Designs for Gas Turbine Engine Testing

1996 ◽  
Author(s):  
Peter D. Smout ◽  
Steven C. Cook
Keyword(s):  
Gas Turbine ◽  
Mechanical Damage ◽  
Engine Performance ◽  
Leading Edge ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Turbine Engine ◽  
Industry Standard ◽  
Repair Costs ◽  
Engine Testing

The determination of gas turbine engine performance relies heavily on intrusive rakes of pilot tubes and thermocouples for gas path pressure and temperature measurement. For over forty years, Kiel-shrouds mounted on the rake body leading edge have been used as the industry standard to de-sensitise the instrument to variations in flow incidence and velocity. This results in a complex rake design which is expensive to manufacture, susceptible to mechanical damage, and difficult to repair. This paper describes an exercise aimed at radically reducing rake manufacture and repair costs. A novel ’common cavity rake’ (CCR) design is presented where the pressure and/or temperature sensors are housed in a single slot let into the rake leading edge. Aerodynamic calibration data is included to show that the performance of the CCR design under uniform flow conditions and in an imposed total pressure gradient is equivalent to that of a conventional Kiel-shrouded rake.

Training Future Gas Turbine Performance Engineers

2007 ◽  
Author(s):  
V. Pachidis ◽  
P. Pilidis ◽  
I. Li
Keyword(s):  
Gas Turbine ◽  
Thermal Power ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Performance Simulation ◽  
Turbine Engine ◽  
Turbine Performance ◽  
Auxiliary Power ◽  
Engine Testing ◽  
The Uk

The performance analysis of modern gas turbine engine systems has led industry to the development of sophisticated gas turbine performance simulation tools and the utilization of skilled operators who must possess the ability to balance environmental, performance and economic requirements. Academic institutions, in their training of potential gas turbine performance engineers have to be able to meet these new challenges, at least at a postgraduate level. This paper describes in detail the “Gas Turbine Performance Simulation” module of the “Thermal Power” MSc course at Cranfield University in the UK, and particularly its practical content. This covers a laboratory test of a small Auxiliary Power Unit (APU) gas turbine engine, the simulation of the ‘clean’ engine performance using a sophisticated gas turbine performance simulation tool, as well as the simulation of the degraded performance of the engine. Through this exercise students are expected to gain a basic understanding of compressor and turbine operation, gain experience in gas turbine engine testing and test data collection and assessment, develop a clear, analytical approach to gas turbine performance simulation issues, improve their technical communication skills and finally gain experience in writing a proper technical report.

Engine Test Experience and Characterization of Self Sealing Ceramic Matrix Composites for Nozzle Applications in Gas Turbine Engines

2003 ◽  
Author(s):  
Eric P. Bouillon ◽  
Patrick C. Spriet ◽  
Georges Habarou ◽  
Thibault Arnold ◽  
Greg C. Ojard ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Elevated Temperatures ◽  
Low Cycle Fatigue ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Turbine Engines ◽  
Matrix Composites ◽  
Gas Turbine Engines ◽  
Sic Fiber ◽  
Engine Testing

Advanced materials are targeting durability improvement in gas turbine engines. One general area of concern for durability is in the hot section components of the engine. Ceramic matrix composites offer improvements in durability at elevated temperatures with a corresponding reduction in weight for nozzles of gas turbine engines. Building on past material efforts, ceramic matrix composites using a carbon and a SiC fiber with a self-sealing matrix have been developed for gas turbine applications. Prior to ground engine testing, a reduced test matrix was undertaken to aggressively test the material in a long-term hold cycle at elevated temperatures and environments. This tensile low cycle fatigue testing was done in air and a 90% steam environment. After completion of the aggressive testing effort, six nozzle seals were fabricated and installed in an F100-PW-229 engine for accelerated mission testing. The C fiber CMC and the SiC Fiber CMC were respectively tested to 600 and 1000 hours in accelerated conditions without damage. Engine testing is continuing to gain additional time and insight with the objective of pursuing the next phase of field service evaluation. Mechanical testing and post-test characterization results of this testing will be presented. The results of the engine testing will be shown and overall conclusions drawn.

Ceramic Composites for Gas Turbine Engines via a New Process

1989 ◽  
Author(s):  
G. H. Schiroky ◽  
A. W. Urquhart ◽  
B. W. Sorenson
Keyword(s):  
Gas Turbine ◽  
Joint Venture ◽  
New Technology ◽  
Ceramic Composites ◽  
Gas Turbine Engine ◽  
Molten Metals ◽  
Oxidation Reactions ◽  
Turbine Engine ◽  
New Process ◽  
Engine Components

A new process for ceramic composites involves the growth of ceramic matrices through shaped preforms using directed oxidation reactions of molten metals. The preforms may consist of reinforcing fibers, whiskers, platelets, or particles, as needed to produce the desired properties in the finished component. This new technology is being developed by Lanxide Corporation and is being applied to gas turbine engine components by Du Pont Lanxide Composites Inc., a joint venture. The paper includes a description of the technology and a discussion of the status of its application to materials for gas turbine engine components.

Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Benny George ◽  
Nagalingam Muthuveerappan
Keyword(s):  
Temperature Measurement ◽  
Gas Turbine ◽  
Measurement Errors ◽  
Gas Turbine Engine ◽  
Critical Parameters ◽  
Turbine Engine ◽  
Design Changes ◽  
Component Efficiency ◽  
Point Pressure ◽  
Engine Testing

Abstract During gas turbine engine testing, steady-state gas-path stagnation temperatures and pressures are measured in order to calculate the adiabatic efficiencies of the major turbomachinery components. These measurements are carried out using fixed intrusive probes, which are installed at the inlet and outlet of each component. The overall uncertainty in calculated component efficiency depends on the accuracy of discrete point pressure and temperature measurement. High accuracy in measurement and prediction of measurement errors has become increasingly important if small gains in component performance needs to be achieved. The recent trend is to predict component efficiencies within ±1–2%. The present work covers different Kiel designs that have been developed in a response to this demand based on a MATLAB code and experimental evaluation. A parametric study has been carried out by varying the two most critical parameters viz. Ae/Ab ratio and L/D ratio to optimize the Kiel design. These design changes will allow measurements to be made with minimum possible errors and efficiencies to be calculated more accurately over a wider range of conditions inside a low bypass turbofan gas turbine engine.

Sign in / Sign up

Export Citation Format

Share Document