GB1028444A - Compressor for a gas turbine engine - Google Patents
Compressor for a gas turbine engineInfo
- Publication number
- GB1028444A GB1028444A GB259965A GB259965A GB1028444A GB 1028444 A GB1028444 A GB 1028444A GB 259965 A GB259965 A GB 259965A GB 259965 A GB259965 A GB 259965A GB 1028444 A GB1028444 A GB 1028444A
- Authority
- GB
- United Kingdom
- Prior art keywords
- compressor
- gas turbine
- tubes
- intermediate casing
- orifices
- 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1,028,444. Axial-flow compressors; gas turbine engines. ROLLS-ROYCE Ltd. Jan. 20, 1965 No. 2599/65. Headings F1C and FIG. In a compressor for a gas turbine engine, surging is prevented by bleeding air from the compressor at, say, the fourth row of stator blades 16 through bleed orifices 17 formed in the inner and intermediate casing walls 14, 13 under the control of a pair of annular tubes 19 of rubber. When inflated, the tubes 19 press against the intermediate casing wall 13 to close the bleed orifices 17. When the tubes are deflated, the bleed air can pass to the space between the outer and intermediate casing walls 12, 13 and thence through ducts 23 to inlet orifices 24 disposed between, say, the inlet guide vanes 22 to re-enter the working duct. A longitudinally corrugated strengthening ring 15 is brazed to the walls 12, 13 at the tips of the corrugations.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB259965A GB1028444A (en) | 1965-01-20 | 1965-01-20 | Compressor for a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB259965A GB1028444A (en) | 1965-01-20 | 1965-01-20 | Compressor for a gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1028444A true GB1028444A (en) | 1966-05-04 |
Family
ID=9742414
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB259965A Expired GB1028444A (en) | 1965-01-20 | 1965-01-20 | Compressor for a gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1028444A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3708242A (en) * | 1969-12-01 | 1973-01-02 | Snecma | Supporting structure for the blades of turbomachines |
| US3909153A (en) * | 1972-09-08 | 1975-09-30 | Bbc Sulzer Turbomaschinen | Multi-stage axial compressor |
| US4844689A (en) * | 1986-07-04 | 1989-07-04 | Rolls-Royce Plc | Compressor and air bleed system |
| GB2220447A (en) * | 1988-07-01 | 1990-01-10 | Schwitzer Us Inc | Gas intake vents for surge and choke control in a compressor |
| US5117629A (en) * | 1989-04-05 | 1992-06-02 | Rolls-Royce Plc | Axial flow compressor |
-
1965
- 1965-01-20 GB GB259965A patent/GB1028444A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3708242A (en) * | 1969-12-01 | 1973-01-02 | Snecma | Supporting structure for the blades of turbomachines |
| US3909153A (en) * | 1972-09-08 | 1975-09-30 | Bbc Sulzer Turbomaschinen | Multi-stage axial compressor |
| US4844689A (en) * | 1986-07-04 | 1989-07-04 | Rolls-Royce Plc | Compressor and air bleed system |
| GB2220447A (en) * | 1988-07-01 | 1990-01-10 | Schwitzer Us Inc | Gas intake vents for surge and choke control in a compressor |
| US5117629A (en) * | 1989-04-05 | 1992-06-02 | Rolls-Royce Plc | Axial flow compressor |
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