GB687365A - Improvements in shock wave compressors, especially for use in connection with continuous flow engines for aircraft - Google Patents
Improvements in shock wave compressors, especially for use in connection with continuous flow engines for aircraftInfo
- Publication number
- GB687365A GB687365A GB13760/50A GB1376050A GB687365A GB 687365 A GB687365 A GB 687365A GB 13760/50 A GB13760/50 A GB 13760/50A GB 1376050 A GB1376050 A GB 1376050A GB 687365 A GB687365 A GB 687365A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shock wave
- blade
- discontinuity
- slot
- curvature
- 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
- F04D21/00—Pump involving supersonic speed of pumped fluids
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
687,365. Axial-flow and helico-centrifugal compressors. OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES (O.N.E.R.A.) June 1, 1950 [June 2, 1949], No. 13760/50. Class 110(i) A compressor comprises at least one bladed element into which the gas enters at supersonic relative velocity, each of the passages between the blades being initially convergent and then divergent, a series of shock waves occurring in the convergent part, the last shock wave being normal to the direction of flow and located at or near the throat of the passage and the first shock wave being oblique and starting from a point of discontinuity in the curvature of the suction side wall of the passage and ending at or near the leading edge of the pressure side wall. Each rotor blade 2 is slotted at 2a, the rear portion having a sharper curvature than the front portion and having its leading edge partly covered by the trailing edge of the front portion. A discontinuity of curvature at a point b of each diffuser blade 1 sets up an oblique shock wave O 1 which ends at the leading edge a of the adjacent blade and is followed by one or more oblique shock waves O 2 and a normal shock wave Op. The flow is supersonic in the convergent part of the diffuser passage ending at the wave Op and subsonic in the subsequent divergent part. The rotor may be of helico-centrifugal form. The sets of blades 1 and 2 may be rotated in opposite directions, as by coupling to the wheels of a contra-rotating gas turbine. Stabilization of a shock wave at a discontinuity of the diffuser blade profile may be effected by sucking the boundary layer through a slot at the discontinuity, the slot being connected to a manifold in communication with a suction fan. Alternatively, the slot may extend through to the opposite side of the blade so that the difference of pressure between the two sides causes air to blow upon the boundary layer at the meeting point of at least two shock waves. In this case, the blade may be formed by two separate elements. Specification 687,338 is referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR687365X | 1949-06-02 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB687365A true GB687365A (en) | 1953-02-11 |
Family
ID=9026075
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB13760/50A Expired GB687365A (en) | 1949-06-02 | 1950-06-01 | Improvements in shock wave compressors, especially for use in connection with continuous flow engines for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB687365A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2841325A (en) * | 1954-05-04 | 1958-07-01 | Snecma | Axial compressors |
| US2931173A (en) * | 1954-08-24 | 1960-04-05 | Richard L Schapker | Compound rotary compressor |
| US2974858A (en) * | 1955-12-29 | 1961-03-14 | Thompson Ramo Wooldridge Inc | High pressure ratio axial flow supersonic compressor |
| US3156407A (en) * | 1958-07-07 | 1964-11-10 | Commissariat Energie Atomique | Supersonic compressors |
| EP0732505A1 (en) * | 1995-03-17 | 1996-09-18 | Research Institute Of Advanced Material Gas-Generator | Rotor blades for axial flow compressor |
| CN102536854A (en) * | 2010-12-21 | 2012-07-04 | 通用电气公司 | A supersonic compressor rotor and methods for assembling same |
-
1950
- 1950-06-01 GB GB13760/50A patent/GB687365A/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2841325A (en) * | 1954-05-04 | 1958-07-01 | Snecma | Axial compressors |
| US2931173A (en) * | 1954-08-24 | 1960-04-05 | Richard L Schapker | Compound rotary compressor |
| US2974858A (en) * | 1955-12-29 | 1961-03-14 | Thompson Ramo Wooldridge Inc | High pressure ratio axial flow supersonic compressor |
| US3156407A (en) * | 1958-07-07 | 1964-11-10 | Commissariat Energie Atomique | Supersonic compressors |
| EP0732505A1 (en) * | 1995-03-17 | 1996-09-18 | Research Institute Of Advanced Material Gas-Generator | Rotor blades for axial flow compressor |
| CN102536854A (en) * | 2010-12-21 | 2012-07-04 | 通用电气公司 | A supersonic compressor rotor and methods for assembling same |
| CN102536854B (en) * | 2010-12-21 | 2016-04-20 | 通用电气公司 | supersonic compressor rotor and assembling method thereof |
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