US3763650A
Expired / Lapsed
US
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Gas turbine temperature profiling structure
Assignee: Westinghouse Electric Corp
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Filing: 1971-07-26
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Granted: 1973-10-09
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Expires: 1991-07-26
Abstract
Abstract An axial flow gas turbine having a structure including a fuel nozzle for providing any desired turbine inlet temperature profile according to the mechanical stress on the rotating turbine blades. The fuel nozzle may be a combined multiple fuel gas and liquid type or a single fuel type, an important feature of both being the provision of fuel injection asymmetrically into the combustion chamber to establish a desired ignited fuel temperature pattern therein which continues down to the turbine inlet. This asymmetrical fuel supply into the combustion chamber is obtained by providing a number or size of fuel jets according to the temperature desired; for example, to provide a temperature gradient decreasing in an inward turbine radial direction through the combustor to correspond to the desired turbine blade inlet temperature profile. The angular jet direction also may be varied for different parts of the fuel injection pattern to obtain a further spatial control of the fuel injection distribution into the combustor. These fuel distribution control variables may be used singly or in any combination, and the same or different ones may be used for the gas and liquid jets in multiple fuel nozzles. In addition, a further modification of the intake temperature profile may be obtained by providing relatively cool jets of gaseous fluid through spaced orifices in the radially inner sides of the transition passages which direct the high temperature working gas to the turbine blades.
Inventors
- 👤 C Hussey
- 👤 S Decorso
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 23:22
CPC Classifications
F; F23; F23D; F23D11/00; F23D11/10; F23D11/101; F23D11/104; F23D11/36; F23D11/38; F23R; F23R3/00; F23R3/28; F23R2900/00; F23R2900/00005
Claims Analysis
Total Claims: 20
Claim 1
Independent Claim
143 words
A high temperature gas supply system for an axial flow turbine having turbine blades arranged to be driven by the high temperature gases and having a combustor with means for igniting fuel supplied thereto, including a fuel supply nozzle comprising a body having a member defining a plurality of fuel outlet spray passages each having a terminal orifice for injecting fuel into the combustor, said terminal orifices being so proportioned that the orifice disposed at the greatest distance from the axis of turbine is larger than the orifice disposed closest to the axis of the turbine and including means for defining a fuel injection pattern for the nozzle of fuel injected into the combustor from said nozzle orifices to provide a substantially predetermined asymmetrical spatial fuel injection pattern transversely of the combustor and a consequent temperature profile of ignited fuel in the combustor.
Claim 2
Dependent Claim
143 words
A high temperature gas supply system for an axial flow turbine having turbine blades arranged to be driven by the high temperature gases and having a combustor with means for igniting fuel supplied thereto, including a fuel supply nozzle comprising a body having a member defining a plurality of fuel outlet spray passages each having a terminal orifice for injecting fuel into the combustor, said terminal orifices being so proportioned that the orifice disposed at the greatest distance from the axis of turbine is larger than the orifice disposed closest to the axis of the turbine and including means for defining a fuel injection pattern for the nozzle of fuel injected into the combustor from said nozzle orifices to provide a substantially predetermined asymmetrical spatial fuel injection pattern transversely of the combustor and a consequent temperature profile of ignited fuel in the combustor.
Claim 3
Dependent Claim
122 words
A fuel nozzle for a turbine combustor adapted to supply hot gases to blades of a gas turbine, comprising a body having a member with a spray face and defining a plurality of angularly outwardly extending fuel outlet spray passages each having a terminal orifice in said spray face for injecting fuel into the combustor, said terminal orifices being so proportioned that the orifice disposed at the greatest distance from the axis of the turbine is larger than the orifice disposed closest to the axis of the turbine and said member defining said orifices arranged relative to each other so as to provide a substantially predetermined asymmetrical fuel injection pattern and a consequent temperature profile of ignited fuel transversely of the combustor.
Claim 4
Dependent Claim
122 words
A fuel nozzle for a turbine combustor adapted to supply hot gases to blades of a gas turbine, comprising a body having a member with a spray face and defining a plurality of angularly outwardly extending fuel outlet spray passages each having a terminal orifice in said spray face for injecting fuel into the combustor, said terminal orifices being so proportioned that the orifice disposed at the greatest distance from the axis of the turbine is larger than the orifice disposed closest to the axis of the turbine and said member defining said orifices arranged relative to each other so as to provide a substantially predetermined asymmetrical fuel injection pattern and a consequent temperature profile of ignited fuel transversely of the combustor.
Claim 5
Dependent Claim
69 words
A fuel nozzle as defined in claim 2 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced and of a larger size for all orifices in substantially the outer semicircle of the spray face corresponding to substantially the outer half of turbine blades fed by the hot gases from said combustor and of a smaller size for orifices in the complementary inner semicircle of the spray face.
Claim 6
Dependent Claim
61 words
A fuel nozzle as defined in claim 2 wherein said member defines said orifices in a progressively graduated size from the smallest at the innermost position of the nozzle orifices relative to the radially inner ends of the turbine blades to the largest orifice at the outermost position of the nozzle orifices relative to said inner ends of the turbine blades.
Claim 7
Dependent Claim
68 words
A fuel nozzle as defined in claim 2 wherein said member defines said spray passages at predetermined different outwardly extending angles relative to The longitudinal center line of the nozzle to provide a predetermined larger fuel injection into the combustor toward the outer side thereof relative to the radially inner ends of the turbine blades and a graduated lesser fuel injection toward the opposite side of the combustor.
Claim 8
Dependent Claim
57 words
A fuel nozzle as defined in claim 2 wherein said member defines said orifices to provide a substantially larger fuel injection by orifices in the outer semicircle of the spray face relative to the radially inner ends of the turbine blades and a predetermined lesser fuel injection by orifices in the complementary semicircle of the spray face.
Claim 9
Dependent Claim
43 words
A fuel nozzle as defined in claim 2 wherein said member defines said orifices to provide a predetermined graduated increase in fuel injection into the combustor from the side thereof nearest to the longitudinal axis of the turbine toward the opposite side thereof.
Claim 10
Dependent Claim
61 words
A fuel nozzle as defined in claim 4 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced at a predetermined angle in the outer semicircle of the spray face relative to the longitudinal axis of the turbine and substantially uniformly circumferentially angularly spaced at a larger angle than said predetermined angle in the complementary semicircle of the spray face.
Claim 11
Dependent Claim
74 words
A fuel nozzle as defined in claim 5 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced and of a larger substantially uniform size for all orifices in substantially the outer semicircle of the spray face corresponding to substantially the radially outer half of turbine blades fed by hot gases from said combustor and of a smaller substantially uniform size for orifices in the complementary inner semicircle of the nozzle spray face.
Claim 12
Dependent Claim
52 words
A fuel nozzle as defined in claim 5 wherein said orifices are arranged in a progressively graduated size from the smallest at the innermost position of the nozzle orifices relative to the longitudinal axis of the turbine to the largest at the outermost position of the nozzle orifices to said turbine axis.
Claim 13
Dependent Claim
61 words
A fuel nozzle as defined in claim 5 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced at a predetermined angle in the outer semicircle of the spray face relative to the longitudinal axis of the turbine and substantially circumferentially angularly spaced at a larger angle than said predetermined angle in the complementary inner semicircle of the spray face.
Claim 14
Dependent Claim
62 words
A fuel nozzle as defined in claim 5 wherein said spray passage angles are a substantially uniform predetermined value relative to the said nozzle center line in the outer semicircle of the spray face relative to the longitudinal axis of the turbine and are a substantially uniform lesser value than said predetermined value in the complementary inner semicircle of the spray face.
Claim 15
Dependent Claim
50 words
A fuel nozzle as defined in claim 5 wherein said spray passage angles are of progressively graduated values from the smallest angle at the innermost passage relative to the longitudinal axis of the turbine to the largest angle at the outermost passage in the nozzle relative to said turbine axis.
Claim 16
Dependent Claim
71 words
A fuel nozzle as defined in claim 2 having a second body surrounding and radially spaced from at least a part of the longitudinal sides of said first mentioned member and defining a cylindrical air flow passage therebetween, means providing for the supply of pressurized air to said cylindrical passage, and means for directing pressurized air from said cylindrical passage around fuel injected into the combustor from said spray passage orifices.
Claim 17
Dependent Claim
55 words
A fuel nozzle as defined in claim 14 wherein said second body includes means defining a plurality of fuel gas outlet passages each having an orifice for injecting pressurized fuel gas into the combustor around fuel injected thereinto from said spray passage orifices, and means for supplying fuel gas to said fuel gas outlet passages.
Claim 18
Dependent Claim
42 words
A Fuel nozzle as defined in claim 15 wherein said fuel gas orifices defining means defines said orifices relative to each other to provide a substantially predetermined asymmetrical fuel gas injection pattern and consequent temperature profile of ignited fuel in the combustor.
Claim 19
Dependent Claim
73 words
A turbine high temperature gas supply system as defined in claim 1 having a plurality of combustors arranged in an annular array and having a plurality of transition structures for transmitting the high temperature gases from the combustors to the turbine blades, said transition structures defining a plurality of circumferentially spaced relatively cool pressurized fluid supply passages for directing relatively cool fluid into the high temperature gases to moderate the temperature profile thereof.
Claim 20
Dependent Claim
46 words
A turbine high temperature gas supply system as defined in claim 20 having means for directing relatively cool fluid into said transition structures'' cool fluid supply directing passages for progressively decreasing the temperature of the high temperature gas in an inward direction radially of the turbine.
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) | 1976-10-08 | 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 |