GB1125658A - Gas turbine by-pass engine - Google Patents
Gas turbine by-pass engineInfo
- Publication number
- GB1125658A GB1125658A GB3042667A GB3042667A GB1125658A GB 1125658 A GB1125658 A GB 1125658A GB 3042667 A GB3042667 A GB 3042667A GB 3042667 A GB3042667 A GB 3042667A GB 1125658 A GB1125658 A GB 1125658A
- Authority
- GB
- United Kingdom
- Prior art keywords
- mixing
- vanes
- gas turbine
- region
- substantially complete
- 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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/383—Introducing air inside the jet with retractable elements
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mixers Of The Rotary Stirring Type (AREA)
Abstract
1,125,658. Mixing gases in conduits. ROLLSROYCE Ltd. 30 June, 1967, No. 30426/67. Heading BIC. [Also in Division F1] To promote mixing of air passing through a by-pass passage 21 of a gas turbine by-pass engine with turbine exhaust gases emerging from an inner casing 12, a mixing device is provided in the region 23 at the outlet of the casing 12. The mixing device comprises a plurality of spaced vanes 30 alternate ones of which are angularly adjustable in opposite directions by means of a rotatable band (35), Fig. 3 (not shown), with slots (34) engaging pegs (33) on the vanes. The band adjusts the vanes between a first position in which they extend axially of the exhaust duct to a second position in which successive pairs form alternate convergent and divergent conduits (31, 32), Fig. 2 (not shown). It is stated that with the vanes in the first position mixing is not substantially complete until the exhaust outlet 24 and in the second position mixing is substantially complete in the region of the reheat combustion equipment 25.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3042667A GB1125658A (en) | 1967-06-30 | 1967-06-30 | Gas turbine by-pass engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3042667A GB1125658A (en) | 1967-06-30 | 1967-06-30 | Gas turbine by-pass engine |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1125658A true GB1125658A (en) | 1968-08-28 |
Family
ID=10307505
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3042667A Expired GB1125658A (en) | 1967-06-30 | 1967-06-30 | Gas turbine by-pass engine |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1125658A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2231092A (en) * | 1989-02-08 | 1990-11-07 | Mtu Muenchen Gmbh | Jet engine |
-
1967
- 1967-06-30 GB GB3042667A patent/GB1125658A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2231092A (en) * | 1989-02-08 | 1990-11-07 | Mtu Muenchen Gmbh | Jet engine |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
ES363673A1 (en) | Outlet housing for an axial-flow turbomachine | |
ES483420A1 (en) | A gas distribution device for the supply of a processing gas to an atomizing chamber. | |
GB1297244A (en) | ||
SE414811B (en) | TURBOFLEKTMOTOR | |
ES421165A1 (en) | Turbine housing | |
IT967469B (en) | AIR INTAKE FOR GAS TURBINE ENGINES | |
GB970189A (en) | Combustion equipment for a gas turbine engine | |
GB1116930A (en) | Improvements in cooled flameholder assembly | |
GB1037923A (en) | Combustion chamber for a gas turbine | |
GB983945A (en) | Improvements in gas turbine engine exhaust system | |
FR1454952A (en) | Improvements to combustion chambers, especially for gas turbine engines | |
GB1090147A (en) | Thrust nozzle for supersonic gas turbine jet engines of the by-pass type | |
GB1125658A (en) | Gas turbine by-pass engine | |
GB922069A (en) | Combustion chamber for a gas turbine engine | |
GB1121361A (en) | Improvements in fluid mixing apparatus | |
GB1038854A (en) | Nozzle assembly for a jet propulsion engine | |
GB1119608A (en) | Jet pipe with variable effective flow cross-sectional area for a gas turbine engine | |
GB910178A (en) | Gas turbine by-pass jet engine | |
GB992931A (en) | Gas turbine jet propulsion engine | |
GB1511849A (en) | Combustion apparatus | |
GB746832A (en) | Jet pipes of gas turbine engines | |
GB1058994A (en) | Improvements in and relating to gas driven turbine assemblies | |
FR1496107A (en) | Variable section intake guide ring for gas turbines | |
GB932000A (en) | Improvements relating to gas turbine engines | |
SE7607544L (en) | DIFFUSER AND FIREPLACE HOUSE FOR GASTURBINE ENGINES |