Patent US3764071A successfully refreshed from Google Patents.
US3764071A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine combustion apparatus
Assignee: UK Secretary of State for Defence
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Filing: 1972-01-31
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Granted: 1973-10-09
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Expires: 1992-01-31
Abstract
Abstract A fuel burner assembly for a gas turbine engine has a number of main fuel ducts each one of which opens cut into an annular duct which surrounds the main fuel nozzle. Air is arranged to flow through the annular duct and completely atomise the main fuel flow and this is particularly the case at low fuel flows when it is sometimes difficult to ensure that complete atomisation takes place.
Inventors
- 👤 R Carlisle
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 21:04
CPC Classifications
F; F23; F23D; F23D11/00; F23D11/10; F23D11/36; F23D17/00; F23D17/002; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/14; F05; F05B; F05B2220/00; F05B2220/30; F05B2220/302
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
133 words
A fuel burner assembly for a gas turbine engine, the burner assembly comprising a main fuel nozzle having a plurality of fuel supply ducts extending therethrough, each of said fuel supply ducts being arranged to receive a supply of fuel, and an annular air supply duct surrounding the main fuel nozzle and having an upstream end for receiving a supply of air and a downstream end, said annular air supply duct being unobstructed and capable of only axial flow of air therethrough, and each of said fuel supply ducts extending through said main fuel nozzle being in communication with said annular air supply duct at a point upstream of the downstream end of said annular air duct whereby atomization of fuel takes place in said annular air duct even at low fuel flow.
Claim 2
Dependent Claim
133 words
A fuel burner assembly for a gas turbine engine, the burner assembly comprising a main fuel nozzle having a plurality of fuel supply ducts extending therethrough, each of said fuel supply ducts being arranged to receive a supply of fuel, and an annular air supply duct surrounding the main fuel nozzle and having an upstream end for receiving a supply of air and a downstream end, said annular air supply duct being unobstructed and capable of only axial flow of air therethrough, and each of said fuel supply ducts extending through said main fuel nozzle being in communication with said annular air supply duct at a point upstream of the downstream end of said annular air duct whereby atomization of fuel takes place in said annular air duct even at low fuel flow.
Claim 3
Dependent Claim
50 words
A fuel burner assembly as claimed in claim 1 in which each of said fuel ducts in said main fuel nozzle comprises two portions, one portion extending in the axial direction and the other portion extending radially and in a downstream direction and opening out into the air supply duct.
Claim 4
Dependent Claim
52 words
A fuel burner assembly as claimed in claim 1 in which the annular air supply duct is formed between the outer surface of the main fuel nozzle and the inner surface of a ring member which is attached to the main fuel nozzle by means of a plurality of radially extending members.
Claim 5
Dependent Claim
66 words
A fuel burner assembly as claimed in claim 1 having a primary fuel nozzle and a primary fuel injector, the primary fuel nozzle being retained in position by the attachment of the main fuel nozzle to a fuel feed arm and the primary fuel injector being retained in position by a spring biassing the primary fuel injector against an abutment face of the primary fuel nozzle.
Claim 6
Dependent Claim
32 words
A fuel burner assembly as claimed in claim 1 including a heat shield attached to the downstream face of said main fuel nozzle and forming with said main fuel nozzle a recess.
Claim 7
Dependent Claim
34 words
A fuel burner assembly as claimed in claim 5 in which a number of ducts connect the annular air supply duct with the recess formed between the main fuel nozzle and the heat shield.
Claim 8
Dependent Claim
126 words
A fuel burner assembly for a gas turbine engine, the burner assembly comprising a main fuel nozzle having a plurality of fuel ducts, each of said ducts being arranged to receive a supply of fuel, an annular air supply duct surrounding said main fuel nozzle, said annular air supply duct being arranged to receive a supply of air and the fuel supply ducts being in communication with the air supply duct, a primary fuel nozzle and a primary fuel injector, said primary fuel nozzle being retained in position by attachment of the main fuel nozzle to a fuel feed arm and the primary fuel injector being retained in position by a spring biasing the primary fuel injector against an abutment face of the primary fuel nozzle.
Claim 9
Dependent Claim
126 words
A fuel burner assembly for a gas turbine engine, the burner assembly comprising a main fuel nozzle having a plurality of fuel ducts, each of said ducts being arranged to receive a supply of fuel, an annular air supply duct surrounding said main fuel nozzle, said annular air supply duct being arranged to receive a supply of air and the fuel supply ducts being in communication with the air supply duct, a primary fuel nozzle and a primary fuel injector, said primary fuel nozzle being retained in position by attachment of the main fuel nozzle to a fuel feed arm and the primary fuel injector being retained in position by a spring biasing the primary fuel injector against an abutment face of the primary fuel nozzle.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-10-08 | 1977-04-09 | 1977-10-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-10-08 | 1981-04-09 | 1981-10-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-10-08 | 1985-04-09 | 1985-10-09 | $7700.00 | Window Closed / Lapsed |