GB706774A - Improvements relating to bearing cooling systems for turbine engines - Google Patents
Improvements relating to bearing cooling systems for turbine enginesInfo
- Publication number
- GB706774A GB706774A GB1895/51A GB189551A GB706774A GB 706774 A GB706774 A GB 706774A GB 1895/51 A GB1895/51 A GB 1895/51A GB 189551 A GB189551 A GB 189551A GB 706774 A GB706774 A GB 706774A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- turbine
- bearing
- chamber
- exhaust
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
- F01D25/125—Cooling of bearings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
706,774. Gas turbine plant. GENERAL MOTORS CORPORATION. Jan. 25, 1951 [Feb. 4, 1950], No. 1895/51. Class 110 (3) The rear bearing of a turbine is cooled by a flow of air induced directly from the atmosphere through radially disposed pipes solely by the flow of gas through the turbine exhaust system. The rear bearing 14 is cooled by air which passes through conduits 40 the ends of which are secured in apertures in the casing extension 41 and the wall 44 of the cooling air chamber 42. From the chamber 42 the air passes through apertures 48 and an annular passage around the bearing to the space between a partition 50 and the turbine wheel 34. The air is drawn out of this space by the action of the gases flowing through the exhaust passage. Air is also drawn from the chamber 42 and led into the exhaust pipe through the aperture 54, the fairing 30, the passage between the struts 38 and conduits 40 and the aperture 43. This air insulates the cooling air supply to the bearing from the hot exhaust gases,
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US706774XA | 1950-02-04 | 1950-02-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB706774A true GB706774A (en) | 1954-04-07 |
Family
ID=22096731
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1895/51A Expired GB706774A (en) | 1950-02-04 | 1951-01-25 | Improvements relating to bearing cooling systems for turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB706774A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2267066A (en) * | 1992-05-16 | 1993-11-24 | Rolls Royce Plc | Vectorable nozzle mounting for VSTOL aircraft |
-
1951
- 1951-01-25 GB GB1895/51A patent/GB706774A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2267066A (en) * | 1992-05-16 | 1993-11-24 | Rolls Royce Plc | Vectorable nozzle mounting for VSTOL aircraft |
| US5348252A (en) * | 1992-05-16 | 1994-09-20 | Rolls-Royce Plc | Vectorable nozzle mounting |
| GB2267066B (en) * | 1992-05-16 | 1995-06-14 | Rolls Royce Plc | Vectorable nozzle mounting |
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