GB649412A - Improvements in rotary compressors and engines - Google Patents
Improvements in rotary compressors and enginesInfo
- Publication number
- GB649412A GB649412A GB2580348A GB2580348A GB649412A GB 649412 A GB649412 A GB 649412A GB 2580348 A GB2580348 A GB 2580348A GB 2580348 A GB2580348 A GB 2580348A GB 649412 A GB649412 A GB 649412A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- discs
- disc
- vanes
- fluid
- 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
- F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
- F01C3/00—Rotary-piston machines or engines with non-parallel axes of movement of co-operating members
- F01C3/02—Rotary-piston machines or engines with non-parallel axes of movement of co-operating members the axes being arranged at an angle of 90 degrees
- F01C3/025—Rotary-piston machines or engines with non-parallel axes of movement of co-operating members the axes being arranged at an angle of 90 degrees of intermeshing engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
649,412. Rotary engines and compressors; gas turbines. STEVENS, A. H. (Wright Aeronautical Corporation). Oct. 4, 1948, No. 25803. [Class 110(ii)] [Also in Group XXII] A rotor 10 is provided with helicospiral vanes 16 which. with abutments 43 on discs 42, form working chambers diminishing in capacity from the rotor periphery radially inwards. The vanes 16 may be hollow, Fig. 1, and have cooling fluid passed through them. A stator 22, supporting the discs 42, is toric-shaped to fit closely to the vane tips, between the discs. The latter ,are driven by main gears 74, 72 frcm the main shaft 76, and from a shaft 66 coupled to the discs through bevel gearing. The stator 22 is built up of segments 32, which carry the discs and their driving mechanism, and segments 34, surrounded by a band 38 secured by bolts 40. The disc axes are tangential to the pitch circle 14 of the toric stator t. The disc shafts 48, 78, carry end flanges 50 and nuts 52 to clamp nut members 54, 56 and the bevel gears in position. Each disc 42 is formed in two halves to facilitate assembly, the halves being secured between the members 54, 56 by screws 62. Each bevel gear 58 meshes with a bevel gear 64 formed integrally with the shaft 66 and gears 60, 84 mesh together. In the construction shown the speed ratio between the rotor 10 and each disc 42 is 12 : 8 to prevent contact between the vanes 16 and disc teeth 43. Labyrinth packings 112, carried by walls 33, 35, minimize leakage of working-fluid, or fluid being compressed, radially inwards. When operating as a compressor the rotor 10 turns anti-clockwise, Fig. 3, and fluid which enters an annular inlet 24 is compressed in the diminishing chambers and discharged through an annular outlet 26. The compression ratio may be varied by varying the number of abutment discs, with increase in the number of vanes 16 and/or increase in the angle subtended by each vane about the rotor axis between the peripheral and minimum diameter of the rotor. Lubricating oil, for the bearings and gears, is supplied through ducts 94, 96, 98, 100. Seals 102 prevent leakage of oil to the discs 42. To balance the axial thrust on the rotor 10, fluid under pressure passes through openings 102 into a chamber 104. Two rotors may be arranged back-to-back for balancing purposes. When the apparatus operates as an engine, high-pressure fluid is supplied through the duct 26. Cooling air may be admitted into a shaft extension 76 and flows into the vane interiors through holes 108 and discharged through holes 110. Where the compressor supplies a gas turbine, compressed air collected by a manifold 114 may be led to passages in or between the turbine blades for cooling purposes. As a rotary engine the apparatus may be used as a starter for aircraft power plants, such as gas turbines. Means to machine the rotor disc, and form the vanes, are described in the Specification.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2580348A GB649412A (en) | 1948-10-04 | 1948-10-04 | Improvements in rotary compressors and engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2580348A GB649412A (en) | 1948-10-04 | 1948-10-04 | Improvements in rotary compressors and engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB649412A true GB649412A (en) | 1951-01-24 |
Family
ID=10233558
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2580348A Expired GB649412A (en) | 1948-10-04 | 1948-10-04 | Improvements in rotary compressors and engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB649412A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2162426A1 (en) * | 1970-12-16 | 1972-06-29 | Jeandel, Ferdinand, Paris; Ets. Pompes Guinard, Saint-Cloud; (Frankreich) | Improvement of motors and compressors with a helical rotor and a closure member engaged with the rotor |
DE2315503A1 (en) * | 1973-03-28 | 1974-10-03 | Omphale Sa | COMPRESSOR OR EXPANSION MACHINE |
DE2950258A1 (en) * | 1978-12-13 | 1980-06-26 | Omphale Sa | COMPRESSION OR RELAXATION MACHINE |
CN103114998A (en) * | 2012-09-29 | 2013-05-22 | 苏州利森空调制冷有限公司 | Compression assembly with dumbbell-shaped rotor for compressor |
-
1948
- 1948-10-04 GB GB2580348A patent/GB649412A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2162426A1 (en) * | 1970-12-16 | 1972-06-29 | Jeandel, Ferdinand, Paris; Ets. Pompes Guinard, Saint-Cloud; (Frankreich) | Improvement of motors and compressors with a helical rotor and a closure member engaged with the rotor |
DE2315503A1 (en) * | 1973-03-28 | 1974-10-03 | Omphale Sa | COMPRESSOR OR EXPANSION MACHINE |
DE2950258A1 (en) * | 1978-12-13 | 1980-06-26 | Omphale Sa | COMPRESSION OR RELAXATION MACHINE |
CN103114998A (en) * | 2012-09-29 | 2013-05-22 | 苏州利森空调制冷有限公司 | Compression assembly with dumbbell-shaped rotor for compressor |
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