GB971443A - Gas turbine by-pass type jet engine - Google Patents
Gas turbine by-pass type jet engineInfo
- Publication number
- GB971443A GB971443A GB29611/63A GB2961163A GB971443A GB 971443 A GB971443 A GB 971443A GB 29611/63 A GB29611/63 A GB 29611/63A GB 2961163 A GB2961163 A GB 2961163A GB 971443 A GB971443 A GB 971443A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pressure compressor
- bleed
- air
- manifold
- duct
- 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
- F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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
971,443. Gas turbine jet propulsion engines. ROLLS-ROYCE Ltd. July 25, 1963, No. 29611/63. Headings FIG and F1J. The invention relates to a gas turbine jet engine of the by-pass type which comprises a low pressure compressor 10, an intermediate pressure compressor 11, a high pressure compressor 12, also combustion equipment 13, a high pressure turbine 14 and a low pressure turbine 15, all arranged in series flow, the low pressure turbine driving the low pressure compressor by means of shaft 20, and the high pressure turbine driving both the intermediate pressure compressor and the high pressure compressor by means of the shaft 21. The downstream end stage 23 of the intermediate pressure compressor has a cross-sectional area open to the flow of compressed air which is at least 1À1 times as great as that of the adjacent upstream end stage of the high pressure compressor. A by-pass duct 22 is provided which receives a portion of air delivered by the low pressure compressor. A bleed air manifold 25 is provided and is arranged to receive a permanent bleed of compressed air from the downstream end stage of the intermediate pressure compressor, a bleed duct 30 communicating with the manifold whereby bleed air may flow to a point of use, there being also valve means for controlling the flow of bleed air from the bleed manifold selectively into either the bleed duct or the by-pass duct. The bleed air manifold comprises a diffuser inlet portion 26 provided with guide vanes 27, and an outlet nozzle portion 32 which communicates with the by-pass duct 22, aerofoil section struts 34 being provided in the outlet portion 32. A valve 31 is provided in the bleed duct 30 and a ring valve 35 having a series of openings 37 is associated with the struts 34 provided in the outlet portion 32, the ring valve being shown in the open position in Fig. 3. When the ring valve is moved to the closed position the openings 37 are moved into the struts 34 and the unapertured portions block flow of air from the manifold 25. The valves 31 and 35 are coupled so that as one is opened the other is closed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB29611/63A GB971443A (en) | 1963-07-25 | 1963-07-25 | Gas turbine by-pass type jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB29611/63A GB971443A (en) | 1963-07-25 | 1963-07-25 | Gas turbine by-pass type jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB971443A true GB971443A (en) | 1964-09-30 |
Family
ID=10294299
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB29611/63A Expired GB971443A (en) | 1963-07-25 | 1963-07-25 | Gas turbine by-pass type jet engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB971443A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5236211A (en) * | 1975-07-19 | 1977-03-19 | Rolls Royce | Gas turbine engine |
| US4068471A (en) * | 1975-06-16 | 1978-01-17 | General Electric Company | Variable cycle engine with split fan section |
| CN103511124A (en) * | 2012-06-28 | 2014-01-15 | 中航商用航空发动机有限责任公司 | Air flow guide device |
| GB2550201A (en) * | 2016-05-13 | 2017-11-15 | Rolls Royce Plc | Gas turbine engine |
-
1963
- 1963-07-25 GB GB29611/63A patent/GB971443A/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4068471A (en) * | 1975-06-16 | 1978-01-17 | General Electric Company | Variable cycle engine with split fan section |
| JPS5236211A (en) * | 1975-07-19 | 1977-03-19 | Rolls Royce | Gas turbine engine |
| JPS574824B2 (en) * | 1975-07-19 | 1982-01-27 | ||
| CN103511124A (en) * | 2012-06-28 | 2014-01-15 | 中航商用航空发动机有限责任公司 | Air flow guide device |
| CN103511124B (en) * | 2012-06-28 | 2016-11-23 | 中航商用航空发动机有限责任公司 | Airflow guiding device |
| GB2550201A (en) * | 2016-05-13 | 2017-11-15 | Rolls Royce Plc | Gas turbine engine |
| GB2550201B (en) * | 2016-05-13 | 2020-01-08 | Rolls Royce Plc | Gas turbine engine |
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