Anti-Icing of Gas Turbine Engine Inlets

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$69,982.00
Award Year:
1994
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
22603
Agency Tracking Number:
22603
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
780 Eden Road, Lancaster, PA, 17601
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
William G. Anderson
(717) 569-6551
Business Contact:
() -
Research Institute:
n/a
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.

* information listed above is at the time of submission.

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