GB882015A - Improvements in and relating to high speed axial flow compressors - Google Patents
Improvements in and relating to high speed axial flow compressorsInfo
- Publication number
- GB882015A GB882015A GB1269657A GB1269657A GB882015A GB 882015 A GB882015 A GB 882015A GB 1269657 A GB1269657 A GB 1269657A GB 1269657 A GB1269657 A GB 1269657A GB 882015 A GB882015 A GB 882015A
- Authority
- GB
- United Kingdom
- Prior art keywords
- relating
- high speed
- axial flow
- flow compressors
- april
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
882,015. Axial-flow compressors. ENGLISH ELECTRIC CO. Ltd. April 11, 1958 [April 18, 1957], No. 12696/57. Class 110 (1). In an axial - flow compressor, the leading edges 7 of the first row of rotor blades are extended in the radial direction as compared with the trailing edges 8 and the length of the preceding stator blades 2. The lengthened leading edges 7 are accommodated by recesses 9 and 10 in the stator and rotor respectively. This construction increases the cross-sectional area of the throat at the entries between consecutive rotor blades, thereby increasing the Mach number at which shock stalling occurs.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1269657A GB882015A (en) | 1957-04-18 | 1957-04-18 | Improvements in and relating to high speed axial flow compressors |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1269657A GB882015A (en) | 1957-04-18 | 1957-04-18 | Improvements in and relating to high speed axial flow compressors |
Publications (1)
Publication Number | Publication Date |
---|---|
GB882015A true GB882015A (en) | 1961-11-08 |
Family
ID=10009426
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1269657A Expired GB882015A (en) | 1957-04-18 | 1957-04-18 | Improvements in and relating to high speed axial flow compressors |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB882015A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2559217A1 (en) * | 1984-02-06 | 1985-08-09 | Gen Electric | AXIAL COMPRESSOR WITH REDUCED DAWN LOSSES |
EP0194957A2 (en) * | 1985-03-11 | 1986-09-17 | United Technologies Corporation | Compressor blade tip seal |
-
1957
- 1957-04-18 GB GB1269657A patent/GB882015A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2559217A1 (en) * | 1984-02-06 | 1985-08-09 | Gen Electric | AXIAL COMPRESSOR WITH REDUCED DAWN LOSSES |
EP0194957A2 (en) * | 1985-03-11 | 1986-09-17 | United Technologies Corporation | Compressor blade tip seal |
EP0194957A3 (en) * | 1985-03-11 | 1987-06-03 | United Technologies Corporation | Compressor blade tip seal |
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