US4249373A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine
Assignee: Rolls Royce PLC
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Filing: 1979-01-22
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Granted: 1981-02-10
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Expires: 1999-01-22
Abstract
Abstract A gas turbine engine comprises an annular combustion chamber (13) intended for low nitrogen oxide emission. The chamber has a pre-mixing section (20) in which an air-fuel mixture is brought to a significant degree of vaporization before issuing through a grill (22) at the end of the pre-mixing section into a main section (21) of the chamber. Pilot sections (18,19) at opposite sides of the pre-mixing section have outlets (28,29) through which burning mixture from the pilot sections is discharged into main section (21). The grill (22) defines openings (35) through which the fresh mixture from the pre-mixing section (20) is discharged across the outlets (28,29) of the pilot sections (18,19) to mix with and become ignited by the burning mixture. The pre-mixing section (20) is an annular duct (33) having walls (15,16) which extend in the direction of the axis of the chamber and are straight in that direction though slightly convergent. The arrangement favors vaporization in the duct without auto-ignition.
Inventors
- 👤 Arthur Sotheran
- 👤 David H. Parnell
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 15:50
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/16; F23R3/18; F23R3/20; F23R3/28; F23R3/34
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
216 words
A gas turbine engine comprising a compressed air delivery duct having an outlet, a combustion chamber having an upstream end wall facing said outlet, a pre-mixing duct defined by side walls extending substantially linearly from said end wall into said chamber and defining a mean direction of flow, the chamber defining pilot sections at opposite sides of the pre-mixing duct and further defining a main section downstream of the pilot sections and of the pre-mixing duct, means provided at said end wall for introducing a pilot mixture of fuel and air into the pilot sections, the pre-mixing duct having an upstream end defining an air inlet opening and positioned to receive air from said outlet of the air delivery duct, the pre-mixing duct further having a downstream end defined by means defining outlet openings dimensioned to restrict flow from the pre-mixing duct and positioned to face across said pilot sections, means for igniting the pilot mixture to generate pilot flame, means for introducing fuel into the pre-mixing duct at said opening thereby to generate in the pre-mixing duct a pre-mixture of fuel and air which is lean compared to the pilot mixture and which is dischargeable through said outlet openings into said pilot flame as the latter passes from said pilot sections into said main section.
Claim 2
Dependent Claim
216 words
A gas turbine engine comprising a compressed air delivery duct having an outlet, a combustion chamber having an upstream end wall facing said outlet, a pre-mixing duct defined by side walls extending substantially linearly from said end wall into said chamber and defining a mean direction of flow, the chamber defining pilot sections at opposite sides of the pre-mixing duct and further defining a main section downstream of the pilot sections and of the pre-mixing duct, means provided at said end wall for introducing a pilot mixture of fuel and air into the pilot sections, the pre-mixing duct having an upstream end defining an air inlet opening and positioned to receive air from said outlet of the air delivery duct, the pre-mixing duct further having a downstream end defined by means defining outlet openings dimensioned to restrict flow from the pre-mixing duct and positioned to face across said pilot sections, means for igniting the pilot mixture to generate pilot flame, means for introducing fuel into the pre-mixing duct at said opening thereby to generate in the pre-mixing duct a pre-mixture of fuel and air which is lean compared to the pilot mixture and which is dischargeable through said outlet openings into said pilot flame as the latter passes from said pilot sections into said main section.
Claim 3
Dependent Claim
113 words
A gas turbine engine according to claim 1 wherein said pre-mixing duct has a downstream end wall extending between said side walls and said pre-mixing duct is curved in the sense of being convex when viewed from said main section, said outlet openings being defined in said pre-mixing duct end wall and being elongate in the direction between said side walls thereby to define end portions facing said pilot sections and a medial portion facing said main section, said pre-mixture in operation emerging from each said outlet opening in the form of a fan extending across the main section at the junction thereof with said pre-mixing duct end wall and said pilot sections.
Claim 4
Dependent Claim
57 words
A gas turbine engine according to claim 1 further comprising means for creating, in each said pilot section, flow of said pilot mixture along the adjacent side wall of the pre-mixing duct and toward the downstream end thereof thereby to promote mixing of the pilot mixture and the pre-mixture at the downstream end of the pre-mixing duct.
Claim 5
Dependent Claim
23 words
A gas turbine engine according to claim 1, wherein said side walls of the pre-mixing duct are mutually convergent in the downstream direction.
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) | 1984-02-10 | 1984-08-11 | 1985-02-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-02-10 | 1988-08-11 | 1989-02-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-02-10 | 1992-08-11 | 1993-02-10 | $7700.00 | Window Closed / Lapsed |