GB651237A - Turbine construction for a turbo-jet engine - Google Patents
Turbine construction for a turbo-jet engineInfo
- Publication number
- GB651237A GB651237A GB30704/48A GB3070448A GB651237A GB 651237 A GB651237 A GB 651237A GB 30704/48 A GB30704/48 A GB 30704/48A GB 3070448 A GB3070448 A GB 3070448A GB 651237 A GB651237 A GB 651237A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- annular
- blades
- hollow
- secured
- 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
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
651,237. Jet propulsion plant. PACKARD MOTOR CAR CO. Nov. 26, 1948, No. 30704. Convention date, Dec. 17, 1947. [Class 110(iii)] In a gas turbine jet-propulsion plant, the nozzle structure comprises hollow guide blades 41 carried by inner and outer rings 40, 44. The ring 44 is secured to the outer casing 22. The ring 40 is secured to an annular part 37. The structure is centred and supported by eight radial pins 50, passing through some of the hollow guide blades, which enter holes in spaced lugs 51 on a coned part 34 of the inner frame. The ring 40 is continued by a ring 54 which closely surrounds the tips of the running blades-53. The ring 54 is carried by a number of radial pins 56 passing through the outer casing and a stiffening ring 47. The ring 54 is grooved to provide annular fins opposite the blade tips. The hollow shaft 24 is open at its up-stream end. It receives air under ram-pressure and conducts the air to radial-passages 27 in the rotor which lead to the hollow of the turbine blades. The annular combustion chamber is of a diameter smaller than the delivery of the centrifugal compressor and is connected thereto by an inturned annular duct.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US651237XA | 1947-12-17 | 1947-12-17 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB651237A true GB651237A (en) | 1951-03-14 |
Family
ID=22060483
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB30704/48A Expired GB651237A (en) | 1947-12-17 | 1948-11-26 | Turbine construction for a turbo-jet engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB651237A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1057827B (en) * | 1955-08-18 | 1959-05-21 | Stroemungsmasch Anst | Fixed impeller rim for gas turbines |
| DE1233209B (en) * | 1957-12-26 | 1967-01-26 | Gen Electric | Gas turbine engine |
-
1948
- 1948-11-26 GB GB30704/48A patent/GB651237A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1057827B (en) * | 1955-08-18 | 1959-05-21 | Stroemungsmasch Anst | Fixed impeller rim for gas turbines |
| DE1233209B (en) * | 1957-12-26 | 1967-01-26 | Gen Electric | Gas turbine engine |
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