GB100072A - Improvements in and relating to the Working of Combustion Turbines. - Google Patents
Improvements in and relating to the Working of Combustion Turbines.Info
- Publication number
- GB100072A GB100072A GB187916A GB187916A GB100072A GB 100072 A GB100072 A GB 100072A GB 187916 A GB187916 A GB 187916A GB 187916 A GB187916 A GB 187916A GB 100072 A GB100072 A GB 100072A
- Authority
- GB
- United Kingdom
- Prior art keywords
- regenerator
- exhaust gases
- pipe
- combustion chamber
- led
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
100,072. Bischof, B. Feb. 8, 1915, [Convention date]. Working-fluid supply. -Relates to combustionproduct turbines wherein the charge is diluted by exhaust gases and is heated in a regenerator 5 by the exhaust gases on its way to the combustion chamber 1, the exhaust gases flowing through the regenerator in an opposite direction and parallel to the new charge, and consists in facilitating the transfer of heat in the regenerator by securing high-pressure conditions, i.e. by arranging that the gases from the combustion chamber do not expand in the nozzles 2 down to atmospheric pressure. After acting on the turbine wheel 3, the gases pass through the regenerator 5, and a portion equal in weight to the charge is led by a pipe 20 to the low-pressure chamber 22 for further action on the wheel 3. The rest of the exhaust gases may be led through a cooler 7 and returned to the regenerator 5 by a compressor delivering into a pipe 16, or conducted further to a regenerator 9, a cooler 11, and forced by a compressor 30 back through the regenerator 9 and so to the regenerator 5 by a pipe 35, where it mixes with compressed air supplied by a compressor 29, the mixture being heated in the regenerator 5 by the exhaust gases and then led to the combustion chamber 1, where it mixes with fuel blown in through a nozzle 28 for flameless surface combustion. The pipe 20 tapping the exhaust gases may be located at any point of the regenerator 5 or in front of the same. When gas is used instead of liquid fuel, it is compressed and regenerated separately before mixing in the combustion chamber. Specifications 2565/95 and 21,320/04 are referred to.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE100072X | 1915-02-08 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB100072A true GB100072A (en) | 1917-04-26 |
Family
ID=5648383
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB187916A Expired GB100072A (en) | 1915-02-08 | 1916-02-08 | Improvements in and relating to the Working of Combustion Turbines. |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB100072A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7168949B2 (en) | 2004-06-10 | 2007-01-30 | Georgia Tech Research Center | Stagnation point reverse flow combustor for a combustion system |
US7425127B2 (en) | 2004-06-10 | 2008-09-16 | Georgia Tech Research Corporation | Stagnation point reverse flow combustor |
-
1916
- 1916-02-08 GB GB187916A patent/GB100072A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7168949B2 (en) | 2004-06-10 | 2007-01-30 | Georgia Tech Research Center | Stagnation point reverse flow combustor for a combustion system |
US7425127B2 (en) | 2004-06-10 | 2008-09-16 | Georgia Tech Research Corporation | Stagnation point reverse flow combustor |
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