GB638103A - Improvements in or relating to gas-turbine power-plant installations - Google Patents
Improvements in or relating to gas-turbine power-plant installationsInfo
- Publication number
- GB638103A GB638103A GB2697147A GB2697147A GB638103A GB 638103 A GB638103 A GB 638103A GB 2697147 A GB2697147 A GB 2697147A GB 2697147 A GB2697147 A GB 2697147A GB 638103 A GB638103 A GB 638103A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- gas
- stages
- compressor
- chambers
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
638,103. Gas turbine plant. RUBBRA, A. A. Oct: 7, 1947, No. 26971. [Class 110(iii)] In a gas turbine power plant installation having a multi-stage turbine, hot gas is abstracted from between a pair of adjacent stages of the turbine for use in the prevention of ice formation or removal of ice from the compressor intake or parts of the compressor. The turbine plant shown comprises a turbine 14 driving a compressor 12 and an airscrew 17 through a reduction gear 16. The engine air intake 20 is formed between an outer wall 22 forming part of the cowling 11 and a fairing 21 supported from the outer wall by struts 23. The leading edge of the cowling 11 and the leading edge of the fairing 21 have annular chambers 25, 28 formed in them which chambers are connected together by ducts 26, 27 and 19. Outlets 25a, 27a and 28a are provided to convey hot gases from the chambers 25, 28 and duct 27 into the air intake 20. These hot gases are supplied from the engine at a point between the high pressure stage 14a an the low pressure stage 14b through conduits 29 and are regulated by valve means 30 which may be manually controlled or automatically controlled by an ice detector or temperature responsive device. An annular collector chamber 37 surrounding the fixed nozzle guide vanes 31 is connected by passages to the turbine annulus. These passages may be formed by drilling the blade platforms or by cutting away a part of the abutting edges of these platforms. If desired, the annular collector chamber 37 may be replaced by a number of ducts leading to the air intake. When applied to a turbine plant of more than two stages, the hot gas is abstracted from between a pair of adjacent stages where the pressure is only sufficient to overcome losses in the distribution system. The stages may also be mounted on separate shafts. Any means may be used to distribute the hot gases in the intake and the methods described in Specifications 636,612, 638,079 and 638,093, [Group XXXIII], are referred to. Specification 578,769 also is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2697147A GB638103A (en) | 1947-10-07 | 1947-10-07 | Improvements in or relating to gas-turbine power-plant installations |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2697147A GB638103A (en) | 1947-10-07 | 1947-10-07 | Improvements in or relating to gas-turbine power-plant installations |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB638103A true GB638103A (en) | 1950-05-31 |
Family
ID=10252081
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2697147A Expired GB638103A (en) | 1947-10-07 | 1947-10-07 | Improvements in or relating to gas-turbine power-plant installations |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB638103A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5429479A (en) * | 1993-03-03 | 1995-07-04 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Stage of vanes free at one extremity |
-
1947
- 1947-10-07 GB GB2697147A patent/GB638103A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5429479A (en) * | 1993-03-03 | 1995-07-04 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Stage of vanes free at one extremity |
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