GB866793A - Improvements in or relating to axial flow compressors - Google Patents
Improvements in or relating to axial flow compressorsInfo
- Publication number
- GB866793A GB866793A GB27211/57A GB2721157A GB866793A GB 866793 A GB866793 A GB 866793A GB 27211/57 A GB27211/57 A GB 27211/57A GB 2721157 A GB2721157 A GB 2721157A GB 866793 A GB866793 A GB 866793A
- Authority
- GB
- United Kingdom
- Prior art keywords
- velocity
- inlet
- rotor
- tangent
- leading edge
- 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
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
- F04D19/028—Layout of fluid flow through the stages
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
866,793. Axial-flow compressors. SOMMARIVA, G. B. Aug. 29,1957 [Sept. 1, 1956], No. 27211/57. Class 110 (1). Each rotor or stator blade of an axial-flow compressor has a thick inlet portion with a convex leading edge 5<SP>1</SP>, a convex surface 9 merging smoothly into the leading edge 5<SP>1</SP> and into a flat surface 10 which is substantially normal to a plane at right angles to the rotor shaft, and a substantially flat surface 11 merging smoothly into the leading edge 51 and into a concave surface 12 which in turn leads into a straight portion 13 which converges towards the surface 10. The relative velocity w 1 at the inlet to each row of rotor blades 5, 6 is parallel to the tangent a, b drawn at the inlet throat l 1 , and the relative outlet velocity w 2 is parallel to the tangent c, d at the outlet. The velocity c 2 at the inlet to the following row of stator blades 7, 8 is parallel to the tangent e, f drawn at the inlet throat l 3 and the outlet velocity is similar in direction to the absolute velocity c 1 at the inlet to the rotor blades 5, 6. The rotor and stator passages diverge downstream of the respective throats l 1 and l 3 so that the velocity decreases.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT866793X | 1956-09-01 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB866793A true GB866793A (en) | 1961-05-03 |
Family
ID=11330663
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB27211/57A Expired GB866793A (en) | 1956-09-01 | 1957-08-29 | Improvements in or relating to axial flow compressors |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB866793A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3773430A (en) * | 1972-03-17 | 1973-11-20 | Ingersoll Rand Co | Gas compressor |
| EP0042044A1 (en) * | 1980-06-13 | 1981-12-23 | M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft | Axial-flow compressor with displaced surge limit |
-
1957
- 1957-08-29 GB GB27211/57A patent/GB866793A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3773430A (en) * | 1972-03-17 | 1973-11-20 | Ingersoll Rand Co | Gas compressor |
| EP0042044A1 (en) * | 1980-06-13 | 1981-12-23 | M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft | Axial-flow compressor with displaced surge limit |
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