GB774059A - Improvements in or relating to combined gas turbine plant and ram-jet units - Google Patents
Improvements in or relating to combined gas turbine plant and ram-jet unitsInfo
- Publication number
- GB774059A GB774059A GB19129/55A GB1912955A GB774059A GB 774059 A GB774059 A GB 774059A GB 19129/55 A GB19129/55 A GB 19129/55A GB 1912955 A GB1912955 A GB 1912955A GB 774059 A GB774059 A GB 774059A
- Authority
- GB
- United Kingdom
- Prior art keywords
- chambers
- jet
- combustion
- gas turbine
- ram
- 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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
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
774,059. Jet propulsion plant. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. July 1, 1955 [Aug. 3, 1954], No. 19129/55. Class 110 (3). [Also in Group XII] A composite gas turbine plant and ram jet unit has one or more auxiliary combustion chambers of relatively small volume arranged in the main combustion chamber of the ram-jet unit which communicate with the main chamber through orifices facing in a direction substantially inclined with respect to the flow through the ram jet, the auxiliary chamber or chambers being fed with fuel and with air tapped from the compressor of the gas turbine plant or other part thereof where the pressure is substantially greater than the ram jet combustion chamber pressure. The ram jet comprises an intake diffuser duct 1, a central part 3 wherein the air is heated by fuel injected through burners 4 and a propulsion nozzle 5. Auxiliary combustion chambers 6 having a small volume and a faired shape are located around the centre line of the combustion chamber 3. Each of these chambers has a burner 7 and receives combustion air from an air compressor 9 through a duct 8. The air compressor 9 forms part of a gas turbine jetpropulsion engine comprising also combustion chambers 10, a gas turbine 11 which drives the air compressor 9 and a propulsion nozzle 12. Reheat fuel may be burnt in the turbine exhaust chamber 13. The combustion gases from the combustion chambers 6 enter the chamber 3 through holes 15 facing in a direction substantially inclined with respect to the flow through the ram jet. The location of the combustion chambers 6 downstream of the burners 4 facilitates the ignition and burning of the fuel injected through these burners. The main flow of fuel to the ram jet may be through either of the sets of burners 4 or 7. For take-off or cruising the turbo-jet is used alone and the valves 8a are then closed. To increase the altitude at which the engine operates auxiliary chambers similar to the chambers 6 may be placed in the combustion chambers 10, and to supply these chambers and the chambers 6 with air from one or more additional compression stages supplied with air from the main compressor 9. The additional compression stages may be driven by the turbine 11 or by a small auxiliary gas turbine. In a modification, the gas turbine jet propulsion engine is placed outside of the ram jet and provided with a variable area jet-propulsion nozzle. The chambers 6 may be replaced by a single annular combustion chamber.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR774059X | 1954-08-03 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB774059A true GB774059A (en) | 1957-05-01 |
Family
ID=9199676
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB19129/55A Expired GB774059A (en) | 1954-08-03 | 1955-07-01 | Improvements in or relating to combined gas turbine plant and ram-jet units |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB774059A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1144060B (en) * | 1960-08-04 | 1963-02-21 | Daimler Benz Ag | Compound engine for aircraft |
| DE1155941B (en) * | 1959-01-02 | 1963-10-17 | Garrett Corp | Engine |
| US3340689A (en) * | 1967-09-12 | Turbojet bypass engine | ||
| EP1445465A1 (en) * | 2003-02-06 | 2004-08-11 | The Boeing Company | Combination of core engine with ramjet engine incorporating swirl augmented combustion |
| US6895756B2 (en) | 2002-09-13 | 2005-05-24 | The Boeing Company | Compact swirl augmented afterburners for gas turbine engines |
| US6968695B2 (en) | 2002-09-13 | 2005-11-29 | The Boeing Company | Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance |
| US7690192B2 (en) | 2007-04-17 | 2010-04-06 | Pratt & Whitney Rocketdyne, Inc. | Compact, high performance swirl combustion rocket engine |
| US7762058B2 (en) | 2007-04-17 | 2010-07-27 | Pratt & Whitney Rocketdyne, Inc. | Ultra-compact, high performance aerovortical rocket thruster |
| US7762077B2 (en) | 2006-12-05 | 2010-07-27 | Pratt & Whitney Rocketdyne, Inc. | Single-stage hypersonic vehicle featuring advanced swirl combustion |
| CN107013367A (en) * | 2017-02-17 | 2017-08-04 | 北京空天技术研究所 | Turbine base double combustion chamber's punching press combined cycle engine |
| US20230323809A1 (en) * | 2022-04-12 | 2023-10-12 | General Electric Company | Combined cycle propulsion system for hypersonic flight |
-
1955
- 1955-07-01 GB GB19129/55A patent/GB774059A/en not_active Expired
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3340689A (en) * | 1967-09-12 | Turbojet bypass engine | ||
| DE1155941B (en) * | 1959-01-02 | 1963-10-17 | Garrett Corp | Engine |
| DE1144060B (en) * | 1960-08-04 | 1963-02-21 | Daimler Benz Ag | Compound engine for aircraft |
| US7168236B2 (en) | 2002-09-13 | 2007-01-30 | United Technologies Corporation | Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance |
| US6895756B2 (en) | 2002-09-13 | 2005-05-24 | The Boeing Company | Compact swirl augmented afterburners for gas turbine engines |
| US6907724B2 (en) | 2002-09-13 | 2005-06-21 | The Boeing Company | Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance |
| US6968695B2 (en) | 2002-09-13 | 2005-11-29 | The Boeing Company | Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance |
| US7137255B2 (en) * | 2002-09-13 | 2006-11-21 | United Technologies Corporation | Compact swirl augmented afterburners for gas turbine engines |
| EP1445465A1 (en) * | 2003-02-06 | 2004-08-11 | The Boeing Company | Combination of core engine with ramjet engine incorporating swirl augmented combustion |
| US7762077B2 (en) | 2006-12-05 | 2010-07-27 | Pratt & Whitney Rocketdyne, Inc. | Single-stage hypersonic vehicle featuring advanced swirl combustion |
| US7690192B2 (en) | 2007-04-17 | 2010-04-06 | Pratt & Whitney Rocketdyne, Inc. | Compact, high performance swirl combustion rocket engine |
| US7762058B2 (en) | 2007-04-17 | 2010-07-27 | Pratt & Whitney Rocketdyne, Inc. | Ultra-compact, high performance aerovortical rocket thruster |
| CN107013367A (en) * | 2017-02-17 | 2017-08-04 | 北京空天技术研究所 | Turbine base double combustion chamber's punching press combined cycle engine |
| CN107013367B (en) * | 2017-02-17 | 2018-07-20 | 北京空天技术研究所 | Turbine base double combustion chamber's punching press combined cycle engine |
| US20230323809A1 (en) * | 2022-04-12 | 2023-10-12 | General Electric Company | Combined cycle propulsion system for hypersonic flight |
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