US3853273A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Axial swirler central injection carburetor
Assignee: General Electric Co
•
Filing: 1973-10-01
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Granted: 1974-12-10
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Expires: 1993-10-01
Abstract
Abstract An improved gas turbine engine fuel carbureting device includes a low pressure fuel tube for delivering fuel to a region located downstream of a cascade of axial, primary swirl vanes. The tip of the fuel tube may be fluted so as to impart swirl to the fuel emanating from radial holes located therein. The primary swirl vanes act to energize the fuel and deposit it on the inner surface of a venturi shroud, which provides a throat section downstream of the fuel tube. A cascade of counterswirl vanes surround the venturi shroud and provide a region of high shear forces which act to finely atomize fuel swirling out of the venturi shroud.
Inventors
- 👤 P Sabla
- 👤 D Bahr
- 👤 J Taylor
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 06:33
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/14; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
153 words
A fuel carbureting device for a gas turbine engine comprising: a support cup having an inlet and an outlet; a venturi shroud surrounding said support cup and cooperating therewith to define an annular flow path therebetween, said shroud having an upstream end, a downstream end, and a throat section located therebetween; a plurality of axial swirl vanes positioned between said support cup and said venturi shroud and adapted to swirl air flowing through said flow path in a first direction; a fuel tube having a first end adapted to receive fuel and a second end positioned within said support cup, a fuel passage extending from said first end to said second end, a plurality of fuel injection holes located near said second end adapted to deliver fuel to the swirled air flow from said axial vanes; and means for generating a counterswirl flow of air at the downstream end of said venturi shroud.
Claim 2
Dependent Claim
153 words
A fuel carbureting device for a gas turbine engine comprising: a support cup having an inlet and an outlet; a venturi shroud surrounding said support cup and cooperating therewith to define an annular flow path therebetween, said shroud having an upstream end, a downstream end, and a throat section located therebetween; a plurality of axial swirl vanes positioned between said support cup and said venturi shroud and adapted to swirl air flowing through said flow path in a first direction; a fuel tube having a first end adapted to receive fuel and a second end positioned within said support cup, a fuel passage extending from said first end to said second end, a plurality of fuel injection holes located near said second end adapted to deliver fuel to the swirled air flow from said axial vanes; and means for generating a counterswirl flow of air at the downstream end of said venturi shroud.
Claim 3
Dependent Claim
66 words
A fuel carbureting device as recited in claim 1 wherein said fuel tube includes a fluted exterior surface which provides a plurality of grooves in said exterior surface adapted to receive air flowing through said inlet of said support cup and fuel from said fuel injection holes, said grooves and said support cup cooperating to swirl fuel from said fuel injection holes in said first direction.
Claim 4
Dependent Claim
45 words
A fuel carbureting device as recited in claim 2 further including a wear collar surrounding said fuel tube in the vicinity of said grooves and cooperating with Said grooves to provide a plurality of passageways between said collar and said exterior surface of said tube.
Claim 5
Dependent Claim
25 words
A fuel carbureting device as recited in claim 3 wherein said wear collar is sized so as to block said outlet of said support cup.
Claim 6
Dependent Claim
35 words
A fuel carbureting device as recited in claim 3 wherein said axial vanes have leading edges and trailing edges, and said wear collar terminates in a plane defined by the trailing edges of said vanes.
Claim 7
Dependent Claim
27 words
A fuel carbureting device as recited in claim 5 wherein said fuel injection holes lie between said wear collar and said throat section of said venturi shroud.
Claim 8
Dependent Claim
27 words
A fuel carbureting device as recited in claim 1 wherein said fuel injection holes lie between said axial vanes and said throat section of said venturi shroud.
Claim 9
Dependent Claim
40 words
A fuel carbureting device as recited in claim 7 wherein said fuel injection holes extend between said fuel passage and said exterior surface of said fuel tube and said holes have approximately equal flow areas along the entire length thereof.
Claim 10
Dependent Claim
54 words
A fuel carbureting device as recited in claim 8 wherein said counterswirl flow generating means comprise a cylinder surrounding said venturi shroud and defining a flow path therebetween and a plurality of vanes adapted to deliver air to said flow path as a vortical flow in a direction opposite that of said first direction.
References Cited (Backward Citations)
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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) | 1977-12-09 | 1978-06-10 | 1978-12-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-12-09 | 1982-06-10 | 1982-12-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-12-09 | 1986-06-10 | 1986-12-10 | $7700.00 | Window Closed / Lapsed |