US3921906A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Infrared suppression system for a gas turbine engine
Assignee: General Electric Co
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Filing: 1974-12-02
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Granted: 1975-11-25
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Expires: 1994-12-02
Abstract
Abstract An infrared suppression system is provided for an aircraft gas turbine engine for reducing the level of emitted infrared radiation from the engine exhaust. The hot exhaust stream emitted from the engine is mixed with the cooling airflows received from a plurality of sources in order to more effectively reduce the level of emitted infrared radiation. In addition, the infrared suppression system prohibits a direct line of sight back into the core engine.
Inventors
- 👤 James Leroy Nye
- 👤 Samuel Rothrock Barr
- 👤 Thomas Chew
- 👤 William Steyer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 12:24
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/78; F02K1/82; F02K1/822; F02K1/825; B; B64; B64D; B64D33/00; B64D33/04; B64D2033/045; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
129 words
An infrared suppressor for a gas turbine engine comprising: an outer casing for receiving the hot engine exhaust stream including an inlet and outlet through which the hot exhaust stream may respectively enter and exit from the outer casing; a liner disposed within the casing and spaced inward therefrom to define a cooling plenum therebetween for receiving a cooling airflow and further including a plurality of slots therein through which the cooling airflow mixes with the hot engine exhaust, and an annular manifold ring upstream of the liner having an inlet for receiving a second cooling airflow from a source other than the source of cooling airflow to the plenum and an annular outlet slot through which the second cooling airflow is ejected into the hot engine exhaust stream.
Claim 2
Dependent Claim
129 words
An infrared suppressor for a gas turbine engine comprising: an outer casing for receiving the hot engine exhaust stream including an inlet and outlet through which the hot exhaust stream may respectively enter and exit from the outer casing; a liner disposed within the casing and spaced inward therefrom to define a cooling plenum therebetween for receiving a cooling airflow and further including a plurality of slots therein through which the cooling airflow mixes with the hot engine exhaust, and an annular manifold ring upstream of the liner having an inlet for receiving a second cooling airflow from a source other than the source of cooling airflow to the plenum and an annular outlet slot through which the second cooling airflow is ejected into the hot engine exhaust stream.
Claim 3
Dependent Claim
36 words
The infrared suppressor of claim 1 wherein the outlet from the infrared suppressor casing is angled with respect to the inlet so as to eliminate any direct line of sight from the outlet to the inlet.
Claim 4
Dependent Claim
108 words
The infrared suppressor of claim 1 wherein the manifold ring is defined generally between an upstream annular wall member, a downstream wall member, an outer circumferential wall member, and an inner circumferential ring membeR, with the inside edge of the downstream wall member spaced apart from the ring member so as to define the annular outlet slot from the manifold, and wherein the inner ring member may be brought into spaced apart relation with the downstream end of the engine to define an annular outlet slot therebetween which provides a means by which a third source of cooling airflow may be ejected into the hot engine exhaust stream.
Claim 5
Dependent Claim
95 words
The infrared suppressor of claim 3 including a transition cowl, the upstream edge of which is contoured to mate with the downstream edge of an aircraft engine nacelle and the downstream edge of which is abutted against a portion of the inlet to the outer casing thereby permitting the outside surface of the aircraft nacelle to be faired into the suppressor casing wherein the remaining portion of the outer casing inlet extends beyond the periphery of the transition cowl to provide an opening for the inlet of ambient cooling ram airflow to the cooling plenum.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-11-24 | 1979-05-26 | 1979-11-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-11-24 | 1983-05-26 | 1983-11-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-11-24 | 1987-05-26 | 1987-11-25 | $7700.00 | Window Closed / Lapsed |