GB704099A - Improvements in or relating to a gas turbine plant - Google Patents
Improvements in or relating to a gas turbine plantInfo
- Publication number
- GB704099A GB704099A GB1939251A GB1939251A GB704099A GB 704099 A GB704099 A GB 704099A GB 1939251 A GB1939251 A GB 1939251A GB 1939251 A GB1939251 A GB 1939251A GB 704099 A GB704099 A GB 704099A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- combustion chambers
- chambers
- air
- increase
- 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
- F02K7/02—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 the jet being intermittent, i.e. pulse-jet
- F02K7/04—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 the jet being intermittent, i.e. pulse-jet with resonant combustion chambers
-
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/10—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
704,099. Gas turbine plant. MASCHINENFABRIK AUGSBURG-NURNBERG AKT.- GES. Aug. 16, 1951 [Aug. 23, 1950], No. 19392/51. Class 110 (3). [Also in Group XII] In a gas turbine plant of the kind described in Specification 701,175 the air supply to the turbine is led through a jacket surrounding the wall or walls of the combustion chamber, before passing into the turbine. A turbine 2 is actuated by the air drawn into the self igniting pulsating combustion chambers 1a, 16, 1c. Fuel is injected into the chambers by pipe 10a, 10b, 10c and ignited by an auxiliary ignition device. This causes positive pressure waves to advance down the chambers to the diffusers 3a, 3b, 3c, where the positive pressure wave is converted into a returning negative pressure wave which causes more air to be sucked into the combustion chambers through non-return valves 6a, 6b, 6c. These valves also prevent a flow in the upstream direction of the positive pressure wave. The air supply to the combustion chambers which is provided by the turbine driven compressor 11 flows through the jacket space 7 around the combustion chambers and is there heated. Fins may be provided on the combustion chamber walls to increase the rate of heat transfer. The combustion chambers may be operated in or out of phase. The length and cross section of the jacket 7 may be selected so that the air in it resonates in conformitv with the combustion chambers. This is stated to increase the heat transfer rate and to increase the pressure drop through the turbine. In a modification only a single combustion chamber is used. The compressor 11 may also be dispensed with. Specification 368,564, [Group XXXIII], also is referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM5700A DE920640C (en) | 1950-08-24 | 1950-08-24 | Internal combustion system with self-priming and self-igniting, pulsating combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB704099A true GB704099A (en) | 1954-02-17 |
Family
ID=7293226
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1939251A Expired GB704099A (en) | 1950-08-24 | 1951-08-16 | Improvements in or relating to a gas turbine plant |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE920640C (en) |
| GB (1) | GB704099A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2237069A (en) * | 1989-10-20 | 1991-04-24 | Kershaw H A | Gas turbine engine |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1133186B (en) * | 1959-11-12 | 1962-07-12 | Schmidt Paul | Method for generating compressed air and thermal energy, preferably in a steam power compressed air system |
| DE1233207B (en) * | 1960-06-29 | 1967-01-26 | Klein Hans Christof | Device for the periodic generation of highly compressed working gas for thermal engines |
| DE1199057B (en) * | 1961-07-11 | 1965-08-19 | Berliner Maschb A G Vormals L | Intermittent water recoil engine |
-
1950
- 1950-08-24 DE DEM5700A patent/DE920640C/en not_active Expired
-
1951
- 1951-08-16 GB GB1939251A patent/GB704099A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2237069A (en) * | 1989-10-20 | 1991-04-24 | Kershaw H A | Gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| DE920640C (en) | 1954-11-25 |
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