GB1440638A - Combustion liners - Google Patents
Combustion linersInfo
- Publication number
- GB1440638A GB1440638A GB5903073A GB5903073A GB1440638A GB 1440638 A GB1440638 A GB 1440638A GB 5903073 A GB5903073 A GB 5903073A GB 5903073 A GB5903073 A GB 5903073A GB 1440638 A GB1440638 A GB 1440638A
- Authority
- GB
- United Kingdom
- Prior art keywords
- zone
- combustion
- air
- fuel
- annular
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
1440638 Gas turbine combustion chamber GENERAL MOTORS CORP 20 Dec 1973 [6 April 1973] 59030/73 Heading F1L A gas turbine combustion chamber comprises an outer casing 3 and an inner liner assembly 4 comprising in sequence from the upstream end, a premix zone 23 with inlet air swirlers 16 and a fuel nozzle 13; a combustion zone 27 with primary combustion air inlets 44 opening into the annular air duct 31 between the double walls 30 defining the combustion zone; a residence zone 42 in which combustion is completed; and a dilution zone 40 including dilution air holes 39 adjacent the turbine inlet 6. The premix zone is operated fuel rich, i.e. the fuel to air ratio is from 2À0 to 2À2 stoichiometric and the combustion zone fuel lean, i.e. the fuel to air ratio is from 0À5 to 0À66 stoichiometric, to reduce the level of emission pollution. Cooling of inner wall 30 is improved by roughening its outer surface and of residence zone wall 34 by a film of air leaving annular duct 31. The invention may also be applied to an annular combustion liner.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US34868173A | 1973-04-06 | 1973-04-06 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1440638A true GB1440638A (en) | 1976-06-23 |
Family
ID=23369086
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB5903073A Expired GB1440638A (en) | 1973-04-06 | 1973-12-20 | Combustion liners |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1440638A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2289530A (en) * | 1994-05-20 | 1995-11-22 | Abb Research Ltd | Method of operating a premixing burner |
| DE4432990A1 (en) * | 1994-09-16 | 1996-03-21 | Abb Management Ag | Stationary gas turbine plant |
| CN117515549A (en) * | 2023-10-13 | 2024-02-06 | 江苏中圣园科技股份有限公司 | Staged combustion surface burner |
-
1973
- 1973-12-20 GB GB5903073A patent/GB1440638A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2289530A (en) * | 1994-05-20 | 1995-11-22 | Abb Research Ltd | Method of operating a premixing burner |
| DE4432990A1 (en) * | 1994-09-16 | 1996-03-21 | Abb Management Ag | Stationary gas turbine plant |
| CN117515549A (en) * | 2023-10-13 | 2024-02-06 | 江苏中圣园科技股份有限公司 | Staged combustion surface burner |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PCNP | Patent ceased through non-payment of renewal fee |