GB624828A - Improvements in or relating to combustion apparatus - Google Patents
Improvements in or relating to combustion apparatusInfo
- Publication number
- GB624828A GB624828A GB18325/47A GB1832547A GB624828A GB 624828 A GB624828 A GB 624828A GB 18325/47 A GB18325/47 A GB 18325/47A GB 1832547 A GB1832547 A GB 1832547A GB 624828 A GB624828 A GB 624828A
- Authority
- GB
- United Kingdom
- Prior art keywords
- space
- walls
- gases
- burners
- holes
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Incineration Of Waste (AREA)
Abstract
624,828. Generating combustion products under pressure. WESTINGHOUSE ELECTRIC INTERNATIONAL CO. July 10, 1947, No. 18325. Convention date, July 18, 1946. [Class 51 (i)] A combustion chamber defined by annular walls 31, 32, Fig. 3, has an annular series of burners 37 directed downstream and primary air holes 40, 41. The burners are separated from the holes 40, 41 by two annular walls 43, 44 having perforations 46, 47. The stream of primary air past the perforations 46, 47 draws gases from the space between the walls 43, 44 and causes a counter-flow of gases from the combustion chamber into that space. The Specification, as open to inspection under Sect. 91, describes another form, Fig. 5 (Cancelled), in which the end wall 36 is imperforate and the primary air is admitted from the surrounding air space through holes 52, 53 into spaces behind annular walls 50, 51. The stream of air past the downstream edges of these walls draws gases out of the closed space surrounding the burners 37 and causes a counter-flow of gases into that space. This subject-matter does not appear in the Specification as accepted.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US624828XA | 1946-07-18 | 1946-07-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB624828A true GB624828A (en) | 1949-06-16 |
Family
ID=22042795
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB18325/47A Expired GB624828A (en) | 1946-07-18 | 1947-07-10 | Improvements in or relating to combustion apparatus |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB624828A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1181004B (en) * | 1959-03-11 | 1964-11-05 | Rolls Royce | Combustion chamber for gas turbine jet engines |
-
1947
- 1947-07-10 GB GB18325/47A patent/GB624828A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1181004B (en) * | 1959-03-11 | 1964-11-05 | Rolls Royce | Combustion chamber for gas turbine jet engines |
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