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Anti-Icing of Gas Turbine Engine Inlets

Award Information

Agency:
National Aeronautics and Space Administration
Branch:
N/A
Award ID:
22603
Program Year/Program:
1994 / SBIR
Agency Tracking Number:
22603
Solicitation Year:
N/A
Solicitation Topic Code:
N/A
Solicitation Number:
N/A
Small Business Information
Thermacore, Inc.
780 Eden Road Lancaster, PA -
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Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No
 
Phase 1
Fiscal Year: 1994
Title: Anti-Icing of Gas Turbine Engine Inlets
Agency: NASA
Contract: N/A
Award Amount: $69,982.00
 

Abstract:

In turboshaft and turbofan gas turbine engines, anti-icing of the cowl currently uses compressor discharge bleed air. Use of this air decreases the net thrust or shaft horsepower, and increases the fuel consumption. This proposal contains an innovative loop pipe method to eliminate the use of bleed air for anti-icing of the turbine engine inlet. Engine cycle analyses predict an increase in shaft horsepower of up to 5% combined with a 5% fuel reduction for an IHPTET Phase II turboshaft engine at 20% Maximum Continuous Power (MCP). Loop pipes are similar to heat pipes, however, loop pipes are self-priming during start-up, significantly increasing reliability. In addition, loop pipes are more easily designed to operate in the turbine engine environment, with its high maneuvering accelerations. Loop heat pipes have already been fabricated with power and gravitational heads that are similar to the anti-icing requirements. The Phase I program objective is to examine two aspects of loop pipes that have not previously been addressed: (1) The ability to turn the loop heat pipe off and on, and (2) the ability to restart against high accelerations.

Principal Investigator:

William G. Anderson
7175696551

Business Contact:

Small Business Information at Submission:

Thermacore, Inc.
780 Eden Road Lancaster, PA 17601

EIN/Tax ID:
DUNS: N/A
Number of Employees: N/A
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No