GB585342A - Compound internal-combustion turbine plant - Google Patents
Compound internal-combustion turbine plantInfo
- Publication number
- GB585342A GB585342A GB1362942A GB1362942A GB585342A GB 585342 A GB585342 A GB 585342A GB 1362942 A GB1362942 A GB 1362942A GB 1362942 A GB1362942 A GB 1362942A GB 585342 A GB585342 A GB 585342A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rings
- jet
- turbine plant
- combustion turbine
- compressor
- 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
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
-
- 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
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
585,342. Gas turbines. ARMSTRONG SIDDELEY MOTORS, Ltd., and HEPPNER, F. A. M. Sept. 29, 1942, No. 13629. [Class 110 (iii)] The blade rings 17, 18, 19 of a contrarotational turbine are carried by independently mounted stage motors 20, 21, 22 of the associated air-compressor. The rings 18, 19 and the corresponding end' rings on the compressor stages 21, 22 are separated by stationary blade rings. The designed speeds of the compressor stages diminish progressively from the highpressure to the low-pressure. The outer turbine rotor 13 may be geared as shown to drive a' shaft 44 or may carry the running blades of a jet-augmenter for use in the jet-propulsion of aircraft. Specifications 585,340 and 585,343 are referred to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1362942A GB585342A (en) | 1942-09-29 | 1942-09-29 | Compound internal-combustion turbine plant |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1362942A GB585342A (en) | 1942-09-29 | 1942-09-29 | Compound internal-combustion turbine plant |
Publications (1)
Publication Number | Publication Date |
---|---|
GB585342A true GB585342A (en) | 1947-02-05 |
Family
ID=10026494
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1362942A Expired GB585342A (en) | 1942-09-29 | 1942-09-29 | Compound internal-combustion turbine plant |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB585342A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2606081A1 (en) * | 1986-10-29 | 1988-05-06 | Snecma | PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES |
EP0395497A1 (en) * | 1989-04-26 | 1990-10-31 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Counter rotating prop-fan engine |
-
1942
- 1942-09-29 GB GB1362942A patent/GB585342A/en not_active Expired
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2606081A1 (en) * | 1986-10-29 | 1988-05-06 | Snecma | PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES |
EP0270403A1 (en) * | 1986-10-29 | 1988-06-08 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Propulsion engine with contrarotating power turbines |
US4765135A (en) * | 1986-10-29 | 1988-08-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas turbine engine |
EP0395497A1 (en) * | 1989-04-26 | 1990-10-31 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Counter rotating prop-fan engine |
FR2646473A1 (en) * | 1989-04-26 | 1990-11-02 | Snecma | ENGINE WITH TRACTRIC CONTROTOTATIVE BLOWERS |
US5105618A (en) * | 1989-04-26 | 1992-04-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Counterrotating fan engine |
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