US3712062A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Cooled augmentor liner
Assignee: General Electric Co
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Filing: 1968-04-17
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Granted: 1973-01-23
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Expires: 1988-04-17
Abstract
Abstract A liner for a combustion zone, particularly the thrust augmentor of a jet engine which has longitudinally spaced circumferential corrugations and slot film cooling means at the radially inward portions of each corrugation. The corrugations minimize stress buildup due to circumferential thermal gradients and provide self-support while the slot cooling means allows such corrugations to be used without overheating of the liner. The cooling means may be formed of a corrugated circumferential strip between liner sections.
Inventors
- 👤 D Nash
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 16:29
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/002; F02; F02K; F02K1/00; F02K1/78; F02K1/82; F02K1/822; F05; F05D; F05D2260/00; F05D2260/20; F05D2260/202; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
139 words
In a liner for a combustion region of a gas turbine engine wherein included within the combustion region are an outer duct, a substantially cylindrical liner disposed within said duct and defining a coolant passageway between said duct and the exterior of said liner, means for providing a pressurized flow of cooling air to said coolant passageway, means for providing a flow of combustion supporting gas to the interior of said liner, the improvement comprising: a. said liner having a plurality of circumferential, substantially continuous corrugations therein, the interior surface of said corrugations defining the interior surface of said liner; and b. slot film cooling means included as part of said liner and located at the radially inward peak of each corrugation to direct cooling air flowing therethrough from said coolant passageway along the interior surface of said liner.
Claim 2
Dependent Claim
139 words
In a liner for a combustion region of a gas turbine engine wherein included within the combustion region are an outer duct, a substantially cylindrical liner disposed within said duct and defining a coolant passageway between said duct and the exterior of said liner, means for providing a pressurized flow of cooling air to said coolant passageway, means for providing a flow of combustion supporting gas to the interior of said liner, the improvement comprising: a. said liner having a plurality of circumferential, substantially continuous corrugations therein, the interior surface of said corrugations defining the interior surface of said liner; and b. slot film cooling means included as part of said liner and located at the radially inward peak of each corrugation to direct cooling air flowing therethrough from said coolant passageway along the interior surface of said liner.
Claim 3
Dependent Claim
26 words
A liner as in claim 1 wherein the ratio of the pitch to the depth of said corrugations is in the range of 40/1 to 10/1.
Claim 4
Dependent Claim
49 words
A liner as in claim 2 wherein the combustion region is a thrust augmentor, said combustion supporting gas is hot turbine exhaust gas, and mixing means is provided at the upstream end of said liner to mix a portion of the cooling air with the hot turbine exhaust gas.
Claim 5
Dependent Claim
32 words
A liner as in claim 3 wherein said slot film cooling means is comprised of a corrugated strip circumferentially positioned between overlapping portions of the liner at the inward corrugation peaks thereof.
Claim 6
Dependent Claim
26 words
A liner as in claim 4 wherein the ratio of the pitch to the depth of said corrugations is in the range of 40/1 - 20/1.
Claim 7
Dependent Claim
26 words
A liner as in claim 4 wherein the ratio of the pitch to the depth of said corrugations is in the range of 20/1 - 10/1.
Claim 8
Dependent Claim
33 words
A liner as in claim 4 wherein the total height of the slots defined by said slot film cooling means is at least equal to 25 percent of the depth of said corrugations.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-01-23 | 1976-07-24 | 1977-01-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-01-23 | 1980-07-24 | 1981-01-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-01-23 | 1984-07-24 | 1985-01-23 | $7700.00 | Window Closed / Lapsed |