GB834975A - Afterburner installation - Google Patents
Afterburner installationInfo
- Publication number
- GB834975A GB834975A GB15495/58A GB1549558A GB834975A GB 834975 A GB834975 A GB 834975A GB 15495/58 A GB15495/58 A GB 15495/58A GB 1549558 A GB1549558 A GB 1549558A GB 834975 A GB834975 A GB 834975A
- Authority
- GB
- United Kingdom
- Prior art keywords
- chamber
- fuel
- gutter
- gas
- manifold
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
834,975. Generating combustion products under pressure. LANG, R. A. B. May 14, 1958 [July 23, 1957], No. 15495/58. Class 51 (1). A gas turbine engine exhaust gas reheater comprises combustion apparatus having wall means secured to the tail cone and defining a chamber open in the downstream direction, a gutter surrounding the chamber which contains a fuel manifold, a first fuel ejector associated with the manifold to discharge fuel into the gutter, a second fuel ejector to discharge fuel axially downstream of the chamber, and means to deliver combustion supporting gas to the chamber. The reheater shown in Fig. 1 comprises an exhaust duct 12 containing a tail cone 11, a chamber 13 open in the downstream direction and a gutter 31 surrounding the chamber. The chamber contains a fuel manifold 19 which ejects fuel into the gutter via pipe 28 and also axially downstream of the chamber via pipe 34. Combustion supporting gas is delivered to the chamber through a duct 44, the mixture of fuel and gas on leaving the chamber passes through swirl vanes 37. In a modification. Fig. 2 (not shown), combustion supporting gas for the chamber is supplied from an external source through a radial duct which also carries the fuel supply pipe. This air may be bled from the compressor or be ram air.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US834975XA | 1957-07-23 | 1957-07-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB834975A true GB834975A (en) | 1960-05-18 |
Family
ID=22178726
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB15495/58A Expired GB834975A (en) | 1957-07-23 | 1958-05-14 | Afterburner installation |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB834975A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3059498A1 (en) * | 2015-02-20 | 2016-08-24 | United Technologies Corporation | Angled main mixer for axially controlled stoichiometry combustor |
-
1958
- 1958-05-14 GB GB15495/58A patent/GB834975A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3059498A1 (en) * | 2015-02-20 | 2016-08-24 | United Technologies Corporation | Angled main mixer for axially controlled stoichiometry combustor |
| US10060629B2 (en) | 2015-02-20 | 2018-08-28 | United Technologies Corporation | Angled radial fuel/air delivery system for combustor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| GB618493A (en) | Improvements in or relating to a gas reaction propulsion unit | |
| GB1478395A (en) | Apparatus for supplying a mixture of fuel and air to a combustion chamber | |
| GB840054A (en) | A device for generating power gases for driving power plants such as turbines | |
| GB1303123A (en) | ||
| GB588847A (en) | Improvements in combustion chambers for internal combustion turbines | |
| GB809300A (en) | Improvements relating to combustion chambers for combustion turbines, jet propulsionengines and the like | |
| GB1222747A (en) | Method and apparatus for effecting gas flow through a combustion gas generator | |
| GB992304A (en) | Apparatus for supplying air to a blast furnace | |
| GB834975A (en) | Afterburner installation | |
| GB922069A (en) | Combustion chamber for a gas turbine engine | |
| GB887829A (en) | Improvements relating to flame tubes for combustion systems | |
| GB847500A (en) | Improvements in piping systems or channels for the passage of fluids | |
| GB699166A (en) | Improvements in or relating to gas turbine plants | |
| GB847359A (en) | Supersonic centripetal compressor | |
| GB702752A (en) | Improvements relating to combustion equipment of gas turbine engines | |
| GB811892A (en) | Improvements in combustion devices for continuous-flow internal-combustion machines | |
| GB898368A (en) | Improved combustion chamber | |
| GB744178A (en) | Improvements relating to combustion equipment of gas-turbine engines | |
| GB864517A (en) | Gas turbine engine | |
| GB754847A (en) | Improvements in or relating to combustion apparatus | |
| GB921398A (en) | Aircraft | |
| GB780835A (en) | Improvements relating to combustion equipment for gas-turbine engines and fuel injection means therefor | |
| GB579511A (en) | Improvements in or relating to jet-propulsion apparatus for aircraft | |
| GB842197A (en) | Improvements in afterburner combustion equipment of a gas turbine jet propulsion engine | |
| GB713422A (en) | Improvements relating to combustion equipment for gas turbine engines |