US5197290A
Expired / Lapsed
US
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Variable area combustor air swirler
Assignee: Fuel Systems Textron Inc
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Filing: 1990-03-26
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Granted: 1993-03-30
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Expires: 2010-03-26
Abstract
Abstract The gas turbine combustor air swirler includes a spring temper swirler member having a plurality of air control doors or vanes so cut therein about the longitudinal axis of the combustor inlet as to be integrally and resiliently pivotally connected to the swirler member. The air control doors are progressively canted open to provide predetermined air flow rate and air swirl angle to the combustor inlet in response to increases in air pressure differential thereacross resulting from progressive increases in fuel flow through the nozzle during various regimes of engine operation. The swirler is free of linkages and sliding or other contacting components that are susceptible to binding and other malfunctions in service in the engine.
Inventors
- 👤 Fei P. Lee
- 👤 Theodore R. Koblish
- 👤 Robert M. Halvorsen
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 23:18
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/26; F23R3/04; F23R3/10; F23R3/12; F23R3/14; Y; Y10; Y10T; Y10T137/00; Y10T137/7722; Y10T137/7837; Y10T137/7879; Y10T137/7888; Y10T137/7891
Claims Analysis
Total Claims: 24
Claim 1
Independent Claim
125 words
In combination, a gas turbine engine combustor having an inlet, a fuel nozzle cooperatively disposed relative to the inlet for supplying fuel to the combustor and a variable area air swirler cooperatively disposed relative to the inlet for admitting air to the combustor from a compressor, said swirler comprising a swirler member having a plurality of air control doors so formed therein as to have a side integrally and resiliently pivotally connected to said swirler member to define a door hinge axis such that said doors are progressively canted relative to said swirler member for providing a predetermined air flow rate and air swirl angle in response to variations in air pressure differential across the swirler resulting from variations in fuel flow through the nozzle.
Claim 2
Dependent Claim
125 words
In combination, a gas turbine engine combustor having an inlet, a fuel nozzle cooperatively disposed relative to the inlet for supplying fuel to the combustor and a variable area air swirler cooperatively disposed relative to the inlet for admitting air to the combustor from a compressor, said swirler comprising a swirler member having a plurality of air control doors so formed therein as to have a side integrally and resiliently pivotally connected to said swirler member to define a door hinge axis such that said doors are progressively canted relative to said swirler member for providing a predetermined air flow rate and air swirl angle in response to variations in air pressure differential across the swirler resulting from variations in fuel flow through the nozzle.
Claim 3
Dependent Claim
19 words
The combination of claim 1 wherein each air control door is defined by an incision in the swirler member.
Claim 4
Dependent Claim
35 words
The combination of claim 1 wherein said air control doors each are so formed as to have an elongated side integrally and resiliently pivotally connected to the swirler member to define the door hinge axis.
Claim 5
Dependent Claim
68 words
The combination of claim 1 wherein the swirler member comprises a tubular member having a longitudinal axis generally parallel with a longitudinal axis of the combustor inlet, said air control doors being so formed in said tubular member as to be spaced apart around the longitudinal axis thereof and as to have the door hinge axis of each door generally parallel with the longitudinal axis of the inlet.
Claim 6
Dependent Claim
13 words
The combination of claim 1 wherein the swirler member comprises spring temper metal.
Claim 7
Dependent Claim
28 words
The combination of claim 1 wherein the swirler member and the air control doors formed thereon have a wall thickness of about 0.001 inch to about 0.010 inch.
Claim 8
Dependent Claim
25 words
The combination of claim 1 wherein the nozzle is an airblast nozzle having an air discharge opening disposed axially inwardly of a fuel discharge opening.
Claim 9
Dependent Claim
13 words
The combination of claim 1 wherein the nozzle is a pressure atomizing nozzle.
Claim 10
Dependent Claim
14 words
The combination of claim 1 wherein the nozzle is a hybrid airblast/pressure atomizing nozzle.
Claim 11
Dependent Claim
49 words
The combination of claim 7 wherein said airblast nozzle comprises an airblast fuel injector mounted on a distensible fuel manifold, said manifold having a pintle that cooperates with a valve seat on the injector to vary fuel flow through the injector in response to changes in manifold fuel pressure.
Claim 12
Dependent Claim
29 words
The combination of claim 1 including an air swirler shroud so disposed relative to the swirler as to receive said air therefrom and discharge said air into the combustor.
Claim 13
Dependent Claim
149 words
In combination, a gas turbine engine combustor having an upstream inlet with a longitudinal axis, a fuel nozzle cooperatively disposed relative to the inlet for supplying fuel to the combustor and a variable area air swirler cooperatively disposed relative to the inlet for admitting air to the combustor from an upstream compressor, said swirler comprising a spring temper swirler member having a plurality of air control doors disposed about said longitudinal axis and so formed in said support member as to have a side integrally and resiliently pivotally connected thereto to define a door hinge axis such that said doors are progressively canted in an open direction or in a closed direction for providing a predetermined air flow rate and air swirl angle in response to respective increases or decreases in air pressure differential across the swirler resulting from respective increases or decreases in fuel flow through the nozzle.
Claim 14
Dependent Claim
149 words
In combination, a gas turbine engine combustor having an upstream inlet with a longitudinal axis, a fuel nozzle cooperatively disposed relative to the inlet for supplying fuel to the combustor and a variable area air swirler cooperatively disposed relative to the inlet for admitting air to the combustor from an upstream compressor, said swirler comprising a spring temper swirler member having a plurality of air control doors disposed about said longitudinal axis and so formed in said support member as to have a side integrally and resiliently pivotally connected thereto to define a door hinge axis such that said doors are progressively canted in an open direction or in a closed direction for providing a predetermined air flow rate and air swirl angle in response to respective increases or decreases in air pressure differential across the swirler resulting from respective increases or decreases in fuel flow through the nozzle.
Claim 15
Dependent Claim
19 words
The combination of claim 12 wherein each air control door is defined by an incision in the swirler member.
Claim 16
Dependent Claim
35 words
The combination of claim 12 wherein said air control doors each are so formed as to have an elongated side integrally and resiliently pivotally connected to the swirler member to define the door hinge axis.
Claim 17
Dependent Claim
68 words
The combination of claim 13 wherein the swirler member comprises a tubular member having a longitudinal axis generally parallel with a longitudinal axis of the combustor inlet, said air control doors being so formed in said tubular member as to be spaced apart around the longitudinal axis thereof and as to have the door hinge axis of each door generally parallel with the longitudinal axis of the inlet.
Claim 18
Dependent Claim
65 words
The combination of claim 12 wherein the swirler member comprises an annular plate having a longitudinal axis generally parallel with a longitudinal axis of the combustor inlet, said air control doors being so formed in said plate as to be spaced apart around said longitudinal axis of said inlet and as to have the door hinge axis transverse to the longitudinal axis of the inlet.
Claim 19
Dependent Claim
13 words
The combination of claim 12 wherein the swirler member comprises spring temper metal.
Claim 20
Dependent Claim
28 words
The combination of claim 12 wherein the swirler member and the air control doors formed thereon have a wall thickness of about 0.001 inch to about 0.010 inch.
Claim 21
Dependent Claim
25 words
The combination of claim 12 wherein the nozzle is an airblast nozzle having an air discharge opening disposed axially inwardly of a fuel discharge opening.
Claim 22
Dependent Claim
49 words
The combination of claim 19 wherein said airblast nozzle comprises an airblast fuel injector mounted on a distensible fuel manifold, said manifold having a pintle that cooperates with a valve seat on the injector to vary fuel flow through the injector in response to changes in manifold fuel pressure.
Claim 23
Dependent Claim
183 words
In combination, a gas turbine engine combustor having an inlet, a fuel nozzle cooperatively disposed relative to the inlet for supplying fuel to the combustor and a variable area air swirler cooperatively disposed relative to the inlet for admitting air to the combustor from a compressor, said swirler comprising an annular swirler plate member having a longitudinal axis generally parallel with a longitudinal axis of the combustor inlet and having plurality of air control doors so formed therein as to have a side integrally and resiliently pivotally connected to said swirler member to define a door hinge axis such that said doors are progressively canted relative to said swirler member for providing a predetermined air flow rate and air swirl angle in response to variations in air pressure differential across the swirler resulting from variations in fuel flow through the nozzle, said air control doors being so formed on said swirler plate member as to be spaced apart around the longitudinal axis of said inlet and as to have the respective door hinge axis oriented transverse to the longitudinal axis of said inlet.
Claim 24
Dependent Claim
183 words
In combination, a gas turbine engine combustor having an inlet, a fuel nozzle cooperatively disposed relative to the inlet for supplying fuel to the combustor and a variable area air swirler cooperatively disposed relative to the inlet for admitting air to the combustor from a compressor, said swirler comprising an annular swirler plate member having a longitudinal axis generally parallel with a longitudinal axis of the combustor inlet and having plurality of air control doors so formed therein as to have a side integrally and resiliently pivotally connected to said swirler member to define a door hinge axis such that said doors are progressively canted relative to said swirler member for providing a predetermined air flow rate and air swirl angle in response to variations in air pressure differential across the swirler resulting from variations in fuel flow through the nozzle, said air control doors being so formed on said swirler plate member as to be spaced apart around the longitudinal axis of said inlet and as to have the respective door hinge axis oriented transverse to the longitudinal axis of said inlet.
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) | 1996-03-29 | 1996-09-28 | 1997-03-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2000-03-29 | 2000-09-28 | 2001-03-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2004-03-29 | 2004-09-28 | 2005-03-30 | $7700.00 | Window Closed / Lapsed |