US3729930A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine
Assignee: Rolls Royce PLC
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Filing: 1970-06-23
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Granted: 1973-05-01
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Expires: 1990-06-23
Abstract
Abstract An industrial gas turbine engine comprises a multi-stage axial compressor, combustion equipment, a multi-stage compressor driving turbine, a power turbine and an exhaust duct, the compressor driving turbine being provided with cooling means to cool the blades of said turbine. The cooling means comprises a flow of steam from the compressor which flows onto the surface of each turbine rotor blade through slots in the rotor rim. The steam also flows over the surface of the turbine rotor between adjacent blades and the space between adjacent blades is filled with a honeycomb material, the cells of which constitute ducts for the flow of steam. The stator vanes of the compressor driving turbine are cooled by steam from a heat exchange means which comprises a supply of pure water to a coil in the exhaust duct and a duct from this coil which is in communication with slots upstream of the nozzle guide vanes, the interiors of the nozzle guide vanes, the slots in the turbine rotor, slots in the engine casing upstream of the stator vanes and the interior of the stator vanes.
Inventors
- 👤 D Williams
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 13:27
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/12; F02C7/16; F01; F01D; F01D5/00; F01D5/02; F01D5/08; F02C7/14; F02C7/141; F05; F05D; F05D2260/00; F05D2260/20; F05D2260/232; F05D2260/2322
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
251 words
A gas turbine comprising a rotor, a row of equiangularly spaced apart rotor blades secured to said rotor, steam generating means, a first cooling fluid supply means arranged to direct cooling fluid at the leading edge of each of said rotor blades so as to form on each rotor blade a layer of cooling fluid which extends over at least a major portion of the surface of the rotor blade, saiD first cooling fluid supply means including a plurality of slots positioned in the radially outer surface of the rotor in front of the leading edge of each blade, each slot communicating with the interior of the rotor and arranged for the flow therethrough of at least a portion of the cooling fluid, said cooling fluid being constituted by the steam from said steam generating means, and a second cooling fluid supply means arranged to direct cooling fluid into the spaces between adjacent rotor blades so as to form a layer of cooling fluid on those parts of the surface of the rotor between the rotor blades, said second cooling fluid supply means including a plurality of ducts within the rotor extending approximately parallel to the means chord lines of the rotor blades, each duct communicating with the interior of the rotor, said rotor having relatively low stress areas between points to which adjacent rotor blades are secured, and a majority of said last-mentioned ducts being constituted by a honeycomb type structure carried in said low stress areas of said rotor.
Claim 2
Dependent Claim
251 words
A gas turbine comprising a rotor, a row of equiangularly spaced apart rotor blades secured to said rotor, steam generating means, a first cooling fluid supply means arranged to direct cooling fluid at the leading edge of each of said rotor blades so as to form on each rotor blade a layer of cooling fluid which extends over at least a major portion of the surface of the rotor blade, saiD first cooling fluid supply means including a plurality of slots positioned in the radially outer surface of the rotor in front of the leading edge of each blade, each slot communicating with the interior of the rotor and arranged for the flow therethrough of at least a portion of the cooling fluid, said cooling fluid being constituted by the steam from said steam generating means, and a second cooling fluid supply means arranged to direct cooling fluid into the spaces between adjacent rotor blades so as to form a layer of cooling fluid on those parts of the surface of the rotor between the rotor blades, said second cooling fluid supply means including a plurality of ducts within the rotor extending approximately parallel to the means chord lines of the rotor blades, each duct communicating with the interior of the rotor, said rotor having relatively low stress areas between points to which adjacent rotor blades are secured, and a majority of said last-mentioned ducts being constituted by a honeycomb type structure carried in said low stress areas of said rotor.
Claim 3
Dependent Claim
37 words
A gas turbine engine as claimed in claim 1 wherein the steam generating means comprises an exhaust heat exchanger connected to receive the combustion products exhausted by the gas turbine engine in heat exchange relationship with water.
Claim 4
Dependent Claim
55 words
A gas turbine as claimed in claim 1 wherein the rotor has at least one further row of equiangularly spaced apart rotor blades secured thereto downstream of the first-mentioned row, each further row of rotor blades being provided with first and second cooling means similar to those associated with the first-mentioned row of rotor blades.
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) | 1976-04-30 | 1976-10-30 | 1977-05-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-04-30 | 1980-10-30 | 1981-05-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-04-30 | 1984-10-30 | 1985-05-01 | $7700.00 | Window Closed / Lapsed |