GB743809A - Ignition means for use in starting gas turbine engines - Google Patents
Ignition means for use in starting gas turbine enginesInfo
- Publication number
- GB743809A GB743809A GB2140853A GB2140853A GB743809A GB 743809 A GB743809 A GB 743809A GB 2140853 A GB2140853 A GB 2140853A GB 2140853 A GB2140853 A GB 2140853A GB 743809 A GB743809 A GB 743809A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- igniter
- chamber
- fuel
- flame tube
- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
-
- 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
- F02C7/26—Starting; Ignition
-
- 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
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
743,809. Lighting burners. ARMSTRONG SIDDELEY MOTORS, Ltd. July 15, 1954 [Aug. 1, 1953], No. 21408/53. Class 75(3). [Also in Group XII] In a gas turbine engine in which the combustion equipment is of the kind having a flame tube disposed within an outer air casing, a flame-producing ignition means comprises an igniter chamber having an outlet communicating with the interior of the flame tube. The igniter chamber has a fuel supply, an igniter and an air supply which is independent of the ambient air and is at such a pressure in relation to the ambient pressure that the outlet of the igniter chamber is "choking" i.e. the pressure ratio across the outlet is such that sonic velocity will be produced in the outlet. In Fig. 1 an annular flame tube 26 is mounted within an air space 23, the flame tube having J-shaped pipes 12 through which a mixture of fuel and primary air is supplied. The igniter chamber 17 is of streamlined cross-section and is disposed in the air space 23, its discharge orifice 25 opening into the flame tube. Fuel is supplied through the pipe 19 and air through the pipe 20 to the nozzle 21 and into the igniter chamber, the air being supplied from a high pressure air bottle through a reducing valve. The mixture of fuel and air is ignited in the chamber by means of an igniter 18. In a second embodiment, a baffle plate is disposed opposite the outlet 25 of the igniter chamber, the baffle having passages therethrough for flow of additional fuel which cools the baffle plate before issuing into the combustion zone within the flame tube. In a further embodiment, the igniter chamber is disposed outside the combustion apparatus and communicates with the flame tube through a duct formed as a diffuser. In Fig. 5, the ignition chamber 17a is disposed on the air casing 37, the discharge orifice of the chamber being at 25a. Opposite the discharge orifice is a venturishaped passage 40 leading into the flame tube, the flame issuing at sonic speed from the outlet 25a inducing air at the inlet 44 of the venturi passage and fuel from the line 42. The air and fuel will become mixed and ignited whereby the igniter flame will be increased and its velocity reduced.
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| BE530786D BE530786A (en) | 1953-08-01 | ||
| GB2140853A GB743809A (en) | 1953-08-01 | 1953-08-01 | Ignition means for use in starting gas turbine engines |
| DEA20798A DE1003515B (en) | 1953-08-01 | 1954-07-22 | Ignition device for starting gas turbines |
| FR1105427D FR1105427A (en) | 1953-08-01 | 1954-07-26 | Ignition device for starting a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2140853A GB743809A (en) | 1953-08-01 | 1953-08-01 | Ignition means for use in starting gas turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB743809A true GB743809A (en) | 1956-01-25 |
Family
ID=10162437
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2140853A Expired GB743809A (en) | 1953-08-01 | 1953-08-01 | Ignition means for use in starting gas turbine engines |
Country Status (4)
| Country | Link |
|---|---|
| BE (1) | BE530786A (en) |
| DE (1) | DE1003515B (en) |
| FR (1) | FR1105427A (en) |
| GB (1) | GB743809A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2405371A1 (en) * | 1977-10-05 | 1979-05-04 | Teledyne Ind | TURBOMOTOR STARTER |
| EP1234963A1 (en) * | 2001-02-22 | 2002-08-28 | ALSTOM (Switzerland) Ltd | Turbomachine ignition device and ignition method |
| CN114151200A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Igniter |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB628366A (en) * | 1947-09-01 | 1949-08-26 | Donald Louis Mordell | Improvements relating to gas turbine engines |
| GB655121A (en) * | 1948-05-19 | 1951-07-11 | Rolls Royce | Improvements relating to ignition means for gas-turbine engines |
| GB686131A (en) * | 1950-06-29 | 1953-01-21 | Rolls Royce | Improvements in or relating to ignition arrangements for gas-turbine engines |
-
0
- BE BE530786D patent/BE530786A/xx unknown
-
1953
- 1953-08-01 GB GB2140853A patent/GB743809A/en not_active Expired
-
1954
- 1954-07-22 DE DEA20798A patent/DE1003515B/en active Pending
- 1954-07-26 FR FR1105427D patent/FR1105427A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2405371A1 (en) * | 1977-10-05 | 1979-05-04 | Teledyne Ind | TURBOMOTOR STARTER |
| EP1234963A1 (en) * | 2001-02-22 | 2002-08-28 | ALSTOM (Switzerland) Ltd | Turbomachine ignition device and ignition method |
| US6729142B2 (en) | 2001-02-22 | 2004-05-04 | Alstom Technology Ltd. | Thermal turbomachine and process for igniting the thermal turbomachine |
| CN114151200A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Igniter |
Also Published As
| Publication number | Publication date |
|---|---|
| FR1105427A (en) | 1955-12-02 |
| BE530786A (en) | |
| DE1003515B (en) | 1957-02-28 |
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