GB711439A - Improvements in the cooling systems of gas-turbines - Google Patents
Improvements in the cooling systems of gas-turbinesInfo
- Publication number
- GB711439A GB711439A GB2862951A GB2862951A GB711439A GB 711439 A GB711439 A GB 711439A GB 2862951 A GB2862951 A GB 2862951A GB 2862951 A GB2862951 A GB 2862951A GB 711439 A GB711439 A GB 711439A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- turbine
- cooling air
- duct
- casing
- 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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Abstract
711,439. Gas turbine plant; nozzles. WIGG. R. E., and RUSTON & HORNSBY, Ltd. Dec. 4, 1952 [Dec. 6, 1951] No. 28629/51. Class 110(3) [Also in Group XII] In a gas turbine plant, a duct for conveying hot gases under pressure. such as the turbine inlet duct 18, Fig. 2, is surrounded by a pressure resistant casing 45 which is closed at one end and communicates with a source of compressed air such as the compressor outlet, its diffuser or the dilution air zone of the combustion chamber. in order to define a stagnant air zone the internal pressure of which approximates to that within the duct and the pressure resistant casing is itself surrounded by an outer casing which communicates with a bleed from the compressor downstream of the outlet so that a flow of cooling air is effected therethrough. The outer casing comprises a structural casing 13 and a skin 46 and is fed with cooling air through passages 38, 50 and 49; the air being discharged through passages 51 in the stator 24 to the atmosphere. Part of the cooling air may be ducted off from the passage 51 for cooling the segmental stator ring 23. Dilution and cooling air are mixed with the combustion products fed to the turbine 21, the exhaust gases therefrom being expanded in a separate power turbine. The relative disposition of the turbine, compressor and combustion chamber aggregates 14, 11, 16 respectively, is as shown in Fig. 1.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US323418A US2712729A (en) | 1951-12-06 | 1952-12-01 | Cooling systems of gas-turbines |
| GB2862951A GB711439A (en) | 1952-12-04 | 1952-12-04 | Improvements in the cooling systems of gas-turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2862951A GB711439A (en) | 1952-12-04 | 1952-12-04 | Improvements in the cooling systems of gas-turbines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB711439A true GB711439A (en) | 1954-06-30 |
Family
ID=10278622
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2862951A Expired GB711439A (en) | 1951-12-06 | 1952-12-04 | Improvements in the cooling systems of gas-turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB711439A (en) |
-
1952
- 1952-12-04 GB GB2862951A patent/GB711439A/en not_active Expired
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| GB618493A (en) | Improvements in or relating to a gas reaction propulsion unit | |
| GB695482A (en) | Improvements in or relating to gas-turbine engines | |
| GB716263A (en) | Improvements in or relating to gas turbine engines | |
| GB774425A (en) | Improvements in or relating to turbine engines | |
| GB801281A (en) | Improvements in or relating to reaction turbines | |
| GB935903A (en) | Gas turbine power plant having centripetal flow compressors and centrifugal flow turbines | |
| GB648647A (en) | Improvements in or relating to heat engines utilising jet drives | |
| GB586554A (en) | Improvements in or relating to turbines | |
| GB711439A (en) | Improvements in the cooling systems of gas-turbines | |
| GB783448A (en) | Improvements in or relating to elastic fluid mechanism such as compressors, turbines, or diffusers | |
| GB563918A (en) | Improvements in or relating to exhaust gas turbo-chargers | |
| GB695891A (en) | Improvements in or relating to gas-turbine engines | |
| GB1354333A (en) | Regenerative gas turbine engines | |
| GB761435A (en) | Improvements in or relating to gas turbine engines | |
| US2750738A (en) | Compound gas turbine plant, including simplified ducting arrangements | |
| GB694414A (en) | Improvements in or relating to internal combustion gas turbine engines | |
| GB847359A (en) | Supersonic centripetal compressor | |
| GB595982A (en) | Improvements in and relating to gas turbines | |
| GB949585A (en) | Improvements in axial flow type gas turbines | |
| GB898368A (en) | Improved combustion chamber | |
| GB716145A (en) | Improvements in aircraft jet propulsion engines including a ducted fan | |
| GB118650A (en) | Improvements in Air or Gas Turbines. | |
| GB654411A (en) | Improvements in or relating to jet propulsion units | |
| GB881816A (en) | Improved gas turbine engine | |
| GB827663A (en) | Internal combustion engines |