SBIR/STTR
Design Concepts for Cooled Ceramic Matrix Composite Turbine Vanes, Phase II
Project Introduction
The work proposed herein is to demonstrate that the higher temperature capabilities of Ceramic Matrix Composites (CMC) can be fully utilized to reduce emissions and improve fuel consumption in gas turbine engines. The work involves closely coupling aerothermal and structural analyses for the first stage vane of a high pressure turbine (HPT). These vanes are actively cooled, typically using film cooling. Ceramic materials have different structural and thermal properties than conventional metals used for the first stage HPT vane. Vane configurations which satisfy CMC structural strength and life constraints, while maintaining vane aerodynamic efficiency and increasing mainstream gas temperature for improved engine performance will be identified. The proposed work will examine modifications to vane internal and external configurations to achieve the desired objectives. Thermal and pressure stresses are equally important, and both will be analyzed. Three dimensional fluid and heat transfer analyses will be used to determine vane aerodynamic performance and heat load distributions.
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Anticipated Benefits
Improvements in SFC for commercial transport aircraft through the application of CMC components would be used by the complete range of gas turbine engines used in military applications. Using CMC components in ground power gas turbines can significantly reduce CO2 emissions. Current combined cycles and future clean coal cycles use gas turbine components, and operate as base load plants. Their continuous operation at maximum power consumes very large quantities of fuel. Even a small improvement in fuel rate, (kg/kW), significantly reduces emissions. Any reduction in the fuel consumption yields substantial cost savings. The combined cycle gas turbine overall pressure ratio is only about half that of an aircraft gas turbine. Consequently, pressure loads are lower. Hence, ground power gas turbines might adopt CMC components in the near future. Recuperated turbines, such as those marketed by Solar Turbines Inc., have high cycle efficiencies, but low overall pressure ratios(less than 20). However, they require a large heat exchanger, which causes the capital cost to be greater than the cost of a simple cycle gas turbine for ground power applications. The efficiency of recuperated turbines improves markedly with a rise in gas temperatures. N&R Engineering intends to provide design and analysis services for the evaluation of CMC components in gas turbine engines. In addition, N&R Engineering would provide these services to operators of these engines.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Glenn Research Center
(GRC)
|
Lead Organization | NASA Center | Cleveland, Ohio |
| N&R Engineering | Supporting Organization | Industry | Parma Heights, Ohio |
Primary U.S. Work Locations
-
Ohio
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Center / Facility:
- Glenn Research Center (GRC)
Responsible Program:
- SBIR/STTR
Project Management
Program Director:
Program Manager:
Project Managers:
Principal Investigator:
Project Duration
Start: Jun 2011
End: May 2013
Technology Maturity (TRL)
| Start: | 3 |
| Current: | 4 |
| Estimated End: | 4 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TX01 Propulsion Systems
- TX01.3 Aero Propulsion
- TX01.3.1 Integrated Systems and Ancillary Technologies
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