Development of high temperature turbine subsystem technology to a ''technology readiness status'': Phase II. Quarterly report
Technology testing of full-size, stationary, hot gas path components including both performance and endurance tests in a simulated turbine environment is a major element of the HTTT Phase II program. The test stand facility and the test specimens design and fabrication are discussed herein. A critical element is the test stand combustor which is being designed similar to the final Test Readiness Vehicle (TRV) combustor design. Supporting tests designed to supply significant data relative to gas-side heat transfer coefficients, deposition and corrosion effects of low-Btu gas, chemical cleanup of low-Btu gas, and coolant channel heat transfer characteristics are included in the Phase II program. The Turbine Simulator facility provides a ''system'' test of long term (250 to 500 hours) operation on real low-Btu gas. An advanced fixed-bed gasifier will be coupled to a state-of-the-art chemical cleanup system. This will be followed by a test combustor and a simulated Stage 1 nozzle. Study layouts are in preparation for the TRV-5 based upon a scaled TRV-7 with 48 Stage 1 vanes. The Stage 1 airfoils are specified as composite structures to maintain the 1000/sup 0/F surface temperatures at the 2600/sup 0/F firing temperature. Significant methods must be developed to construct these composite components. The program details requisite to this development activity are being evaluated. These include copper alloy development, selection of a water-cooling tube alloy, methods of forming cladding skins, and the complex assembly techniques required.
- Research Organization:
- General Electric Co., Schenectady, N.Y. (USA). Gas Turbine Div.
- DOE Contract Number:
- EX-76-C-01-1806
- OSTI ID:
- 5099794
- Report Number(s):
- FE-1806-31
- Country of Publication:
- United States
- Language:
- English
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