GB653636A - Improvements in or relating to combustion chambers for gas turbine driven jet propulsion units or gas turbine power plants - Google Patents
Improvements in or relating to combustion chambers for gas turbine driven jet propulsion units or gas turbine power plantsInfo
- Publication number
- GB653636A GB653636A GB3438/48A GB343848A GB653636A GB 653636 A GB653636 A GB 653636A GB 3438/48 A GB3438/48 A GB 3438/48A GB 343848 A GB343848 A GB 343848A GB 653636 A GB653636 A GB 653636A
- Authority
- GB
- United Kingdom
- Prior art keywords
- gas turbine
- jet propulsion
- air
- relating
- power plants
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/54—Reverse-flow combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
653,636. Gas turbine plant. SOC. RATEAU, and ANXIONNAZ, R. Feb. 5, 1948, No. 3438. Convention date, Feb. 27, 1947. [Class 110(iii)] [Also in Group XII] In a gas turbine plant or a gas turbine jet propulsion unit the air from the compressor k is divided into two parts, viz. firstly primary air which flows in a reverse direction from the compressor and again reverses in direction to enter the flame tube, and secondly, secondary air which is mixed with the combustion gases with no substantial change in the direction of flow, thereby reducing to a minimum the loss of head in the secondary air flow. The secondary air flows through the nozzle boxes a which have distributers or blades c which divide the air into thin jets. The combustion gases flow through the passages l1 separating the nozzle boxes a.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR653636X | 1947-02-27 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB653636A true GB653636A (en) | 1951-05-23 |
Family
ID=9005979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3438/48A Expired GB653636A (en) | 1947-02-27 | 1948-02-05 | Improvements in or relating to combustion chambers for gas turbine driven jet propulsion units or gas turbine power plants |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB653636A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1060667B (en) * | 1955-10-15 | 1959-07-02 | Stroemungsmasch Anst | Combustion device for gas turbines |
-
1948
- 1948-02-05 GB GB3438/48A patent/GB653636A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1060667B (en) * | 1955-10-15 | 1959-07-02 | Stroemungsmasch Anst | Combustion device for gas turbines |
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