US3736746A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Recirculating annular slot fuel/air carbureting system for gas turbine combustors
Assignee: General Electric Co
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Filing: 1971-08-13
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Granted: 1973-06-05
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Expires: 1991-08-13
Abstract
Abstract A combustion system for a gas turbine engine is equipped with a fuel carbureting device which delivers a uniform fuel/air mixture to the primary combustion zone through a continuous annular exit slot. Fuel and air are provided as a continuous tangential flow to an annular premixing chamber, which is configured so as to provide a throat, a diffuser zone, and the annular exit slot. Radial swirl vanes are positioned within the premixing chamber to turn the fuel/air mixture axially, and counterswirl vanes surround the exit slot to provide additional primary combustion air to rapidly mix with the fuel/air mixture and to provide flame stabilization regions around the entire annular combustion chamber. Recirculation of the hot gases in the primary combustion zone is achieved by providing a diffuser zone upstream of the exit slot with a bluff body splitter for radially turning the fuel/air mixture.
Inventors
- 👤 T Dubell
- 👤 J Taylor
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 00:06
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/14
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
136 words
In a fuel carbureting device of the type for use in a gas turbine engine which includes an annular combustion zone wherein a high energy gas stream is generated, said carbureting device including an annular premixing chamber having a continuous annular exit slot, said exit slot being substantially coaxial with said annular combustion zone, a plurality of swirl vanes positioned within said exit slot, means for delivering a fuel and air mixture to said premixing chamber as a tangential flow upstream of said swirl vanes and means for generating a counterswirl flow around said exit slot whereby a continuous annular fuel and air mixture is introduced into the combustion zone, the improvement comprising: means for providing said continuous annular fuel and air mixture with a radial velocity component as it flows through said annular exit slot.
Claim 2
Dependent Claim
136 words
In a fuel carbureting device of the type for use in a gas turbine engine which includes an annular combustion zone wherein a high energy gas stream is generated, said carbureting device including an annular premixing chamber having a continuous annular exit slot, said exit slot being substantially coaxial with said annular combustion zone, a plurality of swirl vanes positioned within said exit slot, means for delivering a fuel and air mixture to said premixing chamber as a tangential flow upstream of said swirl vanes and means for generating a counterswirl flow around said exit slot whereby a continuous annular fuel and air mixture is introduced into the combustion zone, the improvement comprising: means for providing said continuous annular fuel and air mixture with a radial velocity component as it flows through said annular exit slot.
Claim 3
Dependent Claim
46 words
The fuel carbureting device recited in claim 1 wherein said annular premixing chamber includes a generally radially extending upstream wall, an inner wall, and an outer wall, said inner and outer walls extending axially from said upstream wall and converging to form an annular throat section.
Claim 4
Dependent Claim
26 words
The fuel carbureting device recited in claim 2 wherein said means for providing the radial components comprises a diffuser zone located downstream of said annular throat.
Claim 5
Dependent Claim
29 words
The fuel carbureting device recited in claim 3 wherein said diffuser zone is formed by extensions of said inner and outer walls which diverge from said annular throat section.
Claim 6
Dependent Claim
20 words
The fuel carbureting device recited in claim 4 further including a bluff body flow splitter positioned within said throat section.
Claim 7
Dependent Claim
18 words
The fuel carbureting device recited in claim 5 wherein said flow splitter is supported by said swirl vanes.
Claim 8
Dependent Claim
38 words
The fuel carbureting device recited in claim 6 wherein said flow splitter, said swirl vanes, and said inner and outer walls cooperate to form a substantially constant flow area downstream of the throat portion of said swirl vanes.
Claim 9
Dependent Claim
33 words
The fuel carbureting device recited in claim 7 wherein said counterswirl flow generating means comprise cascades of counterswirl vanes connected to said inner and outer walls at or near the downstream ends thereof.
Claim 10
Dependent Claim
37 words
A fuel carbureting device as recited in claim 8 wherein said counterswirl vanes are positioned so as to deliver primary combustion air to the combustion zone in a direction counter that of said fuel and air mixture.
Claim 11
Dependent Claim
172 words
A gas turbine engine including a compressor for generating an annular gas stream, a turbine for driving said compressor, and a combustion system wherein high energy fuel is introduced into said annular gas stream and ignited to produce a high energy gas stream to drive the turbine, said combustion system including an annular combustion zone and a fuel carbureting device for delivering a fuel and air mixture to said combustion zone, said fuel carbureting device comprising: an annular premixing chamber having a continuous annular exit slot, said exit slot being substantially coaxial with said annular combustion zone; a plurality of swirl vanes positioned within said exit slot; means for delivering a fuel and air mixture to said premixing chamber as a tangential flow upstream of said swirl vanes; means for generating a counterswirl air flow around the exit slot whereby a continuous fuel and air mixture is introduced into the combustion zone; and means for providing said fuel and air mixture with radial velocity components as it passes through said exit slot.
Claim 12
Dependent Claim
172 words
A gas turbine engine including a compressor for generating an annular gas stream, a turbine for driving said compressor, and a combustion system wherein high energy fuel is introduced into said annular gas stream and ignited to produce a high energy gas stream to drive the turbine, said combustion system including an annular combustion zone and a fuel carbureting device for delivering a fuel and air mixture to said combustion zone, said fuel carbureting device comprising: an annular premixing chamber having a continuous annular exit slot, said exit slot being substantially coaxial with said annular combustion zone; a plurality of swirl vanes positioned within said exit slot; means for delivering a fuel and air mixture to said premixing chamber as a tangential flow upstream of said swirl vanes; means for generating a counterswirl air flow around the exit slot whereby a continuous fuel and air mixture is introduced into the combustion zone; and means for providing said fuel and air mixture with radial velocity components as it passes through said exit slot.
Claim 13
Dependent Claim
37 words
A gas turbine engine as recited in claim 10 wherein said radial velocity component providing means includes a bluff body flow splitter positioned within said exit slot and a diffuser zone located downstream of said flow splitter.
Claim 14
Dependent Claim
52 words
A gas turbine engine as recited in claim 11 wherein said annular premixing chamber comprises a generally radially extending upstream wall, an inner wall and an outer wall extending axially from said upstream wall, said inner and outer walls converging to form a throat section and thereafter diverging toward said diffuser zone.
Claim 15
Dependent Claim
29 words
A gas turbine engine as recited in claim 12 wherein said means for generating a counterswirl air flow comprise a plurality of counterswirl vanes positioned around said diffuser zone.
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) | 1976-06-04 | 1976-12-04 | 1977-06-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-06-04 | 1980-12-04 | 1981-06-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-06-04 | 1984-12-04 | 1985-06-05 | $7700.00 | Window Closed / Lapsed |