GB637512A - Axial flow compressor - Google Patents
Axial flow compressorInfo
- Publication number
- GB637512A GB637512A GB36855/46A GB3685546A GB637512A GB 637512 A GB637512 A GB 637512A GB 36855/46 A GB36855/46 A GB 36855/46A GB 3685546 A GB3685546 A GB 3685546A GB 637512 A GB637512 A GB 637512A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- impeller
- slots
- casing
- air
- 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
637,512. Axial flow compressors. STALKER, E. A. Dec. 13, 1946, No. 36855. Convention date, June 23, 1941. [Classes 110(i) and 110(iii)] An axial-flow compressor comprises a casing 3 housing'impeller and stator members 2, 3a, having impeller and stator blades 5, which alternate axially of a fluid flow passage 7 in the casing. Each member 2, 3a has a compression inducing duct 10, 14 communicating with the discharge end of the fluid flow passage 7 and with the blades 5, 6 which are hollow and have slots in their surfaces communicating with the respective interiors of the blades. The discharge of air through the slots 11 over the backs of the blades reduces turbulence and enables blades of higher lift to be used to increase the compression action of the compressor. Air flowing through the ducts 10, 14 is cooled by passing through the coolers 15, 16. and the interior of the rotor 2 is cooled by air circulated through the annular passage 22 by the supporting arms 23 and 24.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US637512XA | 1941-06-23 | 1941-06-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB637512A true GB637512A (en) | 1950-05-24 |
Family
ID=22051250
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB36855/46A Expired GB637512A (en) | 1941-06-23 | 1946-12-13 | Axial flow compressor |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB637512A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1042828B (en) * | 1955-10-13 | 1958-11-06 | Bristol Aero Engines Ltd | Axial compressor |
| US2864236A (en) * | 1952-06-05 | 1958-12-16 | Snecma | Method of and means for the control of the air inlet opening of a jet propulsion unit or a gas turbine engine |
-
1946
- 1946-12-13 GB GB36855/46A patent/GB637512A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2864236A (en) * | 1952-06-05 | 1958-12-16 | Snecma | Method of and means for the control of the air inlet opening of a jet propulsion unit or a gas turbine engine |
| DE1042828B (en) * | 1955-10-13 | 1958-11-06 | Bristol Aero Engines Ltd | Axial compressor |
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