GB1321657A - Ducted fan gas turbine jet propulsion engine - Google Patents
Ducted fan gas turbine jet propulsion engineInfo
- Publication number
- GB1321657A GB1321657A GB1321657DA GB1321657A GB 1321657 A GB1321657 A GB 1321657A GB 1321657D A GB1321657D A GB 1321657DA GB 1321657 A GB1321657 A GB 1321657A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fan
- pass
- passage
- pass passage
- turbine
- 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
- 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
- F02K3/065—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 front and aft fans
-
- 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
- F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
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
1321657 Gas turbine ducted fan engines DEFENCE SECRETARY OF STATE FOR 10 Sept 1971 [16 Sept 1970] 44178/70 Heading F1J A by-pass type gas turbine jet engine comprises compressor means, combustion chamber and turbine means, a first fan disposed upstream of the combustion chamber, a second fan, disposed downstream of the combustion chamber, an inner by-pass passage which extends substantially the whole length of the engine, and an outer annular by-pass passage which surrounds at least a portion of the inner passage, the blading of one of the fans extending across only one of the two by-pass passages, the blading of the other fan extending across both of the passages. The engine shown in Fig.1 comprises compressor 2, combustion equipment 4 and H.P. turbine 6 which drives the compressor through shaft 9. The engine comprises also an inner by-pass passage 12 and an outer by-pass passage 16 which is disposed around the upstream end of the inner by-pass passage. A front fan 20 extends across both by-pass passages 12 and 16 while a rear fan 28 extends across the inner by-pass passage 12 only. The two fans are driven by an LP turbine 22, the front fan being driven through shaft 24 and the rear fan being mounted at the tips of the LP turbine blades. In Fig. 2, the outer by-pass 30 is disposed around the downstream end of the inner by-pass passage 12 only while the rear fan 26 extends across both the inner and the outer bypass passages 12 and 30. In both engines, part of the air from the front fan passes to the compressor 2.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4417870 | 1970-09-16 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1321657A true GB1321657A (en) | 1973-06-27 |
Family
ID=10432134
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1321657D Expired GB1321657A (en) | 1970-09-16 | 1970-09-16 | Ducted fan gas turbine jet propulsion engine |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1321657A (en) |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2189844A (en) * | 1986-04-30 | 1987-11-04 | Rolls Royce | Gas turbine engines |
EP0950808A2 (en) * | 1998-04-13 | 1999-10-20 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
EP0952330A2 (en) * | 1998-04-13 | 1999-10-27 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
US6209311B1 (en) | 1998-04-13 | 2001-04-03 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
JP2005155621A (en) * | 2003-11-21 | 2005-06-16 | General Electric Co <Ge> | Rear flade type engine |
ES2342586A1 (en) * | 2008-04-30 | 2010-07-08 | Futur Investment Partners, S.A. | Turbopropulsor aeronautical (Machine-translation by Google Translate, not legally binding) |
ES2370308A1 (en) * | 2008-12-31 | 2011-12-14 | Futur Investment Partners, S.A. | Aeronautical motor. (Machine-translation by Google Translate, not legally binding) |
FR3050485A1 (en) * | 2016-04-26 | 2017-10-27 | Snecma | DOUBLE FLOW TURBOMACHINE |
EP3617059A1 (en) * | 2018-08-22 | 2020-03-04 | Rolls-Royce plc | Turbomachine |
EP3623282A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
EP3623285A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
EP3623284A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
EP3623283A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
-
1970
- 1970-09-16 GB GB1321657D patent/GB1321657A/en not_active Expired
Cited By (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2189844A (en) * | 1986-04-30 | 1987-11-04 | Rolls Royce | Gas turbine engines |
EP0950808A2 (en) * | 1998-04-13 | 1999-10-20 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
EP0952330A2 (en) * | 1998-04-13 | 1999-10-27 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
EP0950808A3 (en) * | 1998-04-13 | 2000-05-24 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
EP0952330A3 (en) * | 1998-04-13 | 2000-05-24 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
US6209311B1 (en) | 1998-04-13 | 2001-04-03 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
JP2005155621A (en) * | 2003-11-21 | 2005-06-16 | General Electric Co <Ge> | Rear flade type engine |
EP1533510A3 (en) * | 2003-11-21 | 2009-02-18 | General Electric Company | Two-spool variable cycle gas turbine engine |
ES2342586A1 (en) * | 2008-04-30 | 2010-07-08 | Futur Investment Partners, S.A. | Turbopropulsor aeronautical (Machine-translation by Google Translate, not legally binding) |
ES2370308A1 (en) * | 2008-12-31 | 2011-12-14 | Futur Investment Partners, S.A. | Aeronautical motor. (Machine-translation by Google Translate, not legally binding) |
FR3050485A1 (en) * | 2016-04-26 | 2017-10-27 | Snecma | DOUBLE FLOW TURBOMACHINE |
EP3617059A1 (en) * | 2018-08-22 | 2020-03-04 | Rolls-Royce plc | Turbomachine |
EP3623282A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
EP3623285A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
EP3623284A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
EP3623283A1 (en) * | 2018-08-22 | 2020-03-18 | Rolls-Royce plc | Turbomachine |
US11247780B2 (en) | 2018-08-22 | 2022-02-15 | Rolls-Royce Plc | Turbomachine having inner and outer fans with hub-tip ratios |
US11306682B2 (en) | 2018-08-22 | 2022-04-19 | Rolls-Royce Plc | Concentric turbomachine with trailing edge |
US11313327B2 (en) | 2018-08-22 | 2022-04-26 | Rolls-Royce Plc | Concentric turbomachine with electric machine |
US11371467B2 (en) | 2018-08-22 | 2022-06-28 | Rolls-Royce Plc | Concentric turbomachine with electric machine |
US11371350B2 (en) | 2018-08-22 | 2022-06-28 | Rolls-Royce Plc | Concentric turbomachine with electric machine |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
CSNS | Application of which complete specification have been accepted and published, but patent is not sealed |