Design Concepts for Cooled Ceramic Matrix Composite Turbine Vanes

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$599,694.00
Award Year:
2011
Program:
SBIR
Phase:
Phase II
Contract:
NNX11CA49C
Award Id:
n/a
Agency Tracking Number:
094938
Solicitation Year:
2009
Solicitation Topic Code:
A2.10
Solicitation Number:
n/a
Small Business Information
OH, Parma Heights, OH, 44130-3821
Hubzone Owned:
N
Minority Owned:
Y
Woman Owned:
N
Duns:
123834959
Principal Investigator:
Robert Boyle
Principal Investigator
(440) 845-7020
rbrjboyle760@gmail.com
Business Contact:
Vinod Nagpal
Business Official
(440) 845-7020
vnagpal@nrengineering.com
Research Institution:
n/a
Abstract
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.

* information listed above is at the time of submission.

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