GB1280715A - Improvements in liquid fuel vaporizing combustion systems - Google Patents
Improvements in liquid fuel vaporizing combustion systemsInfo
- Publication number
- GB1280715A GB1280715A GB53398/69A GB5339869A GB1280715A GB 1280715 A GB1280715 A GB 1280715A GB 53398/69 A GB53398/69 A GB 53398/69A GB 5339869 A GB5339869 A GB 5339869A GB 1280715 A GB1280715 A GB 1280715A
- Authority
- GB
- United Kingdom
- Prior art keywords
- liquid fuel
- cross
- vaporizer
- passages
- central passage
- 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
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
- Production Of Liquid Hydrocarbon Mixture For Refining Petroleum (AREA)
Abstract
1280715 Vaporizer SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 31 Oct 1969 [4 Nov 1968] 53398/69 Heading F4T [Also in Division F1] In a liquid fuel vaporizer, especially for gas turbine installations, a tubular shank 21 has partitions 34a and 34b forming a central passage 35 and flanking side passages 36a and 36b, which are supplied with liquid fuel by injectors 41a and 41b, all the said passages being supplied with primary air which flows in the directions of the arrows A1, A2 and A0. The partitions 34a and 34b have orifices 40a and 40b and the tubular shank 21 has orifices 26a and 26b adjacent to its downstream end and communicating with lateral arms 22a and 22b. The central passage 35 preferably has a cross-section greater than the sum of the cross-sections of the flanking side passages so that complete vaporization of the fuel will not occur until the fuel reaches the lateral arms 22a and 22b. A secondary air supply is provided along the annular extension 29 in the direction of the arrows a. In a gas turbine installation, a plurality of the liquid fuel vaporizers are mounted in a conventional arrangement as in Fig. 1 (not shown) which illustrates the mounting of prior art prevaporizing devices. In another embodiment of vaporizer (Fig. 5a, not shown), the central passage (35) has a circular cross-section and the lateral passages 36a and 36b have semi-annular cross-sections.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR172477 | 1968-11-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1280715A true GB1280715A (en) | 1972-07-05 |
Family
ID=8656455
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB53398/69A Expired GB1280715A (en) | 1968-11-04 | 1969-10-31 | Improvements in liquid fuel vaporizing combustion systems |
Country Status (4)
Country | Link |
---|---|
US (1) | US3626444A (en) |
DE (1) | DE1953671C3 (en) |
FR (1) | FR1590542A (en) |
GB (1) | GB1280715A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2236588A (en) * | 1989-08-31 | 1991-04-10 | Rolls Royce Plc | Fuel vapouriser |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2131790B1 (en) * | 1971-02-19 | 1974-09-27 | Snecma | |
GB1392739A (en) * | 1971-07-16 | 1975-04-30 | Snecma | Devices for pre-vaporising liquid fuel |
FR2189630B1 (en) * | 1972-06-23 | 1980-03-14 | Snecma | |
GB1435083A (en) * | 1972-08-10 | 1976-05-12 | Rolls Royce | Gas turbine engine combustion equipment |
US4005572A (en) * | 1975-04-18 | 1977-02-01 | Giffhorn William A | Gas turbine engine control system |
DE2815916C2 (en) * | 1978-04-13 | 1983-11-03 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Annular combustion chamber with fuel pre-evaporation for gas turbine engines |
GB2112125B (en) * | 1981-12-24 | 1985-06-26 | Rolls Royce | Fuel vapouriser for a gas turbine engine combustion chamber |
US5156002A (en) * | 1990-03-05 | 1992-10-20 | Rolf J. Mowill | Low emissions gas turbine combustor |
US6220034B1 (en) | 1993-07-07 | 2001-04-24 | R. Jan Mowill | Convectively cooled, single stage, fully premixed controllable fuel/air combustor |
US5628182A (en) * | 1993-07-07 | 1997-05-13 | Mowill; R. Jan | Star combustor with dilution ports in can portions |
US5613357A (en) * | 1993-07-07 | 1997-03-25 | Mowill; R. Jan | Star-shaped single stage low emission combustor system |
US5377483A (en) * | 1993-07-07 | 1995-01-03 | Mowill; R. Jan | Process for single stage premixed constant fuel/air ratio combustion |
US5638674A (en) * | 1993-07-07 | 1997-06-17 | Mowill; R. Jan | Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission |
US5572862A (en) * | 1993-07-07 | 1996-11-12 | Mowill Rolf Jan | Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules |
FR2730555B1 (en) * | 1995-02-15 | 1997-03-14 | Snecma | FUEL INJECTION ASSEMBLY FOR GAS TURBINE COMBUSTION CHAMBER |
US5924276A (en) * | 1996-07-17 | 1999-07-20 | Mowill; R. Jan | Premixer with dilution air bypass valve assembly |
US6155819A (en) * | 1998-06-12 | 2000-12-05 | Precision Combustion, Inc. | Dry, low NOx catalytic pilot |
US6925809B2 (en) | 1999-02-26 | 2005-08-09 | R. Jan Mowill | Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities |
FR3066009B1 (en) * | 2017-05-02 | 2020-03-06 | Safran Helicopter Engines | PREVAPORIZATION ROD FOR A TURBOMACHINE |
FR3101696B1 (en) * | 2019-10-08 | 2021-10-29 | Safran Helicopter Engines | PREVAPORIZATION ROD FOR A TURBOMACHINE COMBUSTION CHAMBER |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2982098A (en) * | 1953-04-22 | 1961-05-02 | Power Jets Res & Dev Ltd | Liquid fuel vaporizing combustion systems |
US2956404A (en) * | 1956-10-02 | 1960-10-18 | Avco Mfg Corp | Fuel vaporizer |
-
1968
- 1968-11-04 FR FR172477A patent/FR1590542A/fr not_active Expired
-
1969
- 1969-10-24 DE DE1953671A patent/DE1953671C3/en not_active Expired
- 1969-10-30 US US872605A patent/US3626444A/en not_active Expired - Lifetime
- 1969-10-31 GB GB53398/69A patent/GB1280715A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2236588A (en) * | 1989-08-31 | 1991-04-10 | Rolls Royce Plc | Fuel vapouriser |
US5133192A (en) * | 1989-08-31 | 1992-07-28 | Rolls-Royce Plc | Fuel vaporizer |
GB2236588B (en) * | 1989-08-31 | 1993-08-18 | Rolls Royce Plc | Improved fuel vapouriser |
Also Published As
Publication number | Publication date |
---|---|
US3626444A (en) | 1971-12-07 |
DE1953671C3 (en) | 1979-10-18 |
FR1590542A (en) | 1970-04-13 |
DE1953671B2 (en) | 1979-03-01 |
DE1953671A1 (en) | 1970-05-06 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |