GB696143A - Improvements in or relating to jet-engines and method of operating at increased output - Google Patents
Improvements in or relating to jet-engines and method of operating at increased outputInfo
- Publication number
- GB696143A GB696143A GB28539/50A GB2853950A GB696143A GB 696143 A GB696143 A GB 696143A GB 28539/50 A GB28539/50 A GB 28539/50A GB 2853950 A GB2853950 A GB 2853950A GB 696143 A GB696143 A GB 696143A
- Authority
- GB
- United Kingdom
- Prior art keywords
- oxygen
- injected
- engine
- nozzles
- fuel
- 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
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
- F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
-
- 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
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
- F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
696,143. Generating combustion products under pressure. UNITED AIRCRAFT CORPORATION. Nov. 22, 1950 [Dec. 2, 1949]. No.. 28539/50. Class 51(i) [Also in Group XXVI] In a gas turbine jet propulsion engine in which the turbine exhaust gases are 'reheated by the injection of additional fuel, pure oxygen, liquid oxygen or hydrogen peroxide is injected into the engine to complete the burning of the additional fuel. The exhaust gases from the turbine 3 are reheated in a combustion chamber formed between conical members 21, 23 into which fuel is injected through nozzles 27. To ensure complete burning of this fuel oxygen is injected into the reheat chamber through nozzles 33. If desired, the oxygen may be injected ahead of the compressor 2 or main combustion chamber 13. The oxygen may be in the form of pure oxygen, liquid oxygen or hydrogen peroxide. Oxygen from the tank 41 passes through a stop valve 46, pump 45, control valve 57 and manifold 35 to the nozzles 33. The valve 57 may be controlled manually or by a mechanism 58 responsive to the airflow through the engine. The mechanism 58 comprises a spring loaded diaphragm 63, subject on opposite sides to the pressure at the suction and discharge side of the compressor 2. To enable the amount of reheat fuel to be increased without increasing the temperature of the gases coolant may be injected into the engine through nozzles 37. The supply of coolant may be manually controlled or controlled by a valve operated by the mechanism 58. The coolant may be injected into the engine intake or into the combustion chamber.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US696143XA | 1949-12-02 | 1949-12-02 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB696143A true GB696143A (en) | 1953-08-26 |
Family
ID=22090113
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB28539/50A Expired GB696143A (en) | 1949-12-02 | 1950-11-22 | Improvements in or relating to jet-engines and method of operating at increased output |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB696143A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2117053A (en) * | 1982-02-18 | 1983-10-05 | Boc Group Plc | Gas turbines and engines |
| FR2635826A1 (en) * | 1988-09-01 | 1990-03-02 | Mtu Muenchen Gmbh | METHOD FOR FUEL SUPPLYING A TURBO-STATOREACTOR AND TURBO-STATOREACTOR FOR IMPLEMENTING THE PROCESS |
| CN111911315A (en) * | 2020-07-13 | 2020-11-10 | 潍坊联信增压器股份有限公司 | Small micro turbojet engine |
| US10906619B2 (en) | 2016-09-06 | 2021-02-02 | North Actionsports B.V. | Load distribution harness, in particular for water sports |
-
1950
- 1950-11-22 GB GB28539/50A patent/GB696143A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2117053A (en) * | 1982-02-18 | 1983-10-05 | Boc Group Plc | Gas turbines and engines |
| FR2635826A1 (en) * | 1988-09-01 | 1990-03-02 | Mtu Muenchen Gmbh | METHOD FOR FUEL SUPPLYING A TURBO-STATOREACTOR AND TURBO-STATOREACTOR FOR IMPLEMENTING THE PROCESS |
| US10906619B2 (en) | 2016-09-06 | 2021-02-02 | North Actionsports B.V. | Load distribution harness, in particular for water sports |
| CN111911315A (en) * | 2020-07-13 | 2020-11-10 | 潍坊联信增压器股份有限公司 | Small micro turbojet engine |
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