EP0444811A1 - Brennstoffeinspritzvorrichtung - Google Patents

Brennstoffeinspritzvorrichtung Download PDF

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Publication number
EP0444811A1
EP0444811A1 EP91301296A EP91301296A EP0444811A1 EP 0444811 A1 EP0444811 A1 EP 0444811A1 EP 91301296 A EP91301296 A EP 91301296A EP 91301296 A EP91301296 A EP 91301296A EP 0444811 A1 EP0444811 A1 EP 0444811A1
Authority
EP
European Patent Office
Prior art keywords
fuel
annular wall
passage
annular
air
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.)
Withdrawn
Application number
EP91301296A
Other languages
English (en)
French (fr)
Inventor
Eric Carr
Andrew Neil Irwin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Aero & Industrial Technology Ltd
Original Assignee
Aero & Industrial Technology Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Aero & Industrial Technology Ltd filed Critical Aero & Industrial Technology Ltd
Publication of EP0444811A1 publication Critical patent/EP0444811A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • This invention relates to a fuel injector and is particularly, though not exclusively, concerned with a fuel injector for a gas turbine engine.
  • a fuel injector comprising a hollow, generally cylindrical body having a downstream outlet end, an inner annular wall or sleeve having an outwardly flared inner surface defining a downstream end region of an inner air passage in the body, an outer annular wall surrounding the inner annular wall and spaced therefrom so as to define a thin annular fuel passage between the said walls.
  • the outer annular wall has a downstream end terminating at the downstream outlet end of the body and having an outer surface defining part of the inner surface of an outer air passage.
  • a plurality of inclined fuel supply holes open into the annular fuel passage whereby, in use, fuel having a swirl imparted thereto is discharged into the annular fuel passage.
  • the inclined fuel supply holes are provided in the outer annular wall and discharge from the outside inwardly into the annular fuel passage with the object of providing a substantially single annular flow of fuel on the internal surface of the outer annular wall.
  • the swirling fuel then proceeds as a film along the annular fuel passage to contact air from the inner air passage at a location which is substantially half way between the position of the fuel supply holes and the downstream end of the outer wall.
  • the film of fuel then continues along the inner surface of the outer annular wall along with the air from the inner air passage before being discharged through the downstream outlet end of the body and atomised as a result of a shearing effect between air which has passed through the inner air passage and air which has passed through the outer air passage.
  • a fuel injector comprising a hollow, generally cylindrical body having a downstream end, an inner annular wall having an outwardly flared inner surface defining a downstream end region of an inner air passage in the body, an outer annular wall surrounding the inner annular wall and spaced therefrom so as to define an annular fuel passage between said walls, said outer annular wall having a downstream end terminating at the downstream outlet end of the body and having an outer surface defining an inner surface of an outer air passage, and one or more inclined fuel supply holes opening into the annular fuel passage whereby, in use, fuel having a swirl imparted thereto is discharged into the annular fuel passage, forms a film on the inner surface of the outer wall and is subsequently mixed with air passing through the inner and outer air passages; wherein the fuel supply holes are provided in the inner wall so as to discharge outwardly of the latter into the annular fuel passage, and wherein the outwardly flared inner surface of the inner wall terminates adjacent said downstream outlet end of the body and is directed towards the downstream end
  • the arrangement of fuel supply hole(s) which discharge outwardly into the annular fuel passage causes the fuel to impinge against the inner surface of the outer annular wall which lies opposite the holes so that a more effective film of fuel on said inner surface can be established.
  • the termination of the outwardly flared inner surface of the inner wall at or closely adjacent the downstream end of the body ensures that the film of fuel does not have to travel in an exposed condition for a long distance, with the result that carbon formation is mitigated.
  • the above-described arrangement enables the air from the inner air passage to meet the fuel at or adjacent the location at which the fuel meets the air from the outer air passage, thereby leading to improved atomization of the fuel.
  • the inner surface of the outer annular wall is substantially cylindrical.
  • the inner surface of the outer annular wall tapers slightly inwardly towards the outlet end of the body. In such an embodiment, it is preferred for the distance between the inner and outer annular walls to reduce towards the outlet end of the body.
  • the outer surface of the outer annular wall may also converge towards the outlet end of the body.
  • the present invention is particularly applicable to fuel injectors wherein means are provided for imparting a swirl to at least the air which passes through the inner air passage and, more preferably, both air passages.
  • Such swirl may be in the same or opposite sense to the swirl imparted to the fuel.
  • the fuel supply holes which may take the form of bores, slots or gaps in the inner annular wall, are inclined so as to impart a swirl to the fuel passing therethrough in the circumferential direction relative to the annular fuel passage.
  • such fuel supply holes may be directed so as to discharge fuel into the annular fuel passage in an upstream direction, or they may discharge fuel outwardly against a region of the outer surface of the fuel passage which lies in the same plane as the fuel supply holes.
  • the fuel injector illustrated therein is for mounting in a wall 10 of a combustor of a gas turbine engine.
  • the fuel injector comprises a composite, generally cylindrical hollow body 12 having a support arm 14.
  • the body 12 has an inner air inlet 16 at an upstream end thereof and a downstream outlet end 18. Adjacent the inner air inlet 16 there is provided a central boss 20 carrying a series of swirler blades 22 disposed so as to impart a swirl to air entering the body 12 through the inlet 16.
  • the body 12 further comprises a relatively thick inner annular wall 24 having an outwardly flared inner surface 26 defining a downstream end region of an inner air passage 28 passing through the body 12 from the inlet 16 to terminate just short of the outlet end 18 of the body 12.
  • the inner wall 24 is defined partly by inner wall part 24a and partly by inner wall part 24b.
  • the body 12 further includes a relatively thin outer annular wall 30 which surrounds the inner annular wall 24 and is spaced therefrom so as to define an annular fuel passage 32 therebetween.
  • the outer annular wall 30 has a shallow flared downstream end 34 terminating at the outlet end 18 of the body 12.
  • the inner surface of the outer annular wall 30 is cylindrical for most of its length, with the axis of the cylinder being coincident with the longitudinal axis of the body 12.
  • the outer surface of the outer annular wall 30 defines the inner surface of an outer air passage 36 defined between swirler blades 38 mounted so as to extend between the outer annular wall 30 and an outer annular sleeve 40.
  • the outer annular sleeve 40 serves to locate the downstream end of the fuel injector in the wall 10.
  • the inner surface 42 of the sleeve 40 is cylindrical, having its axis coincident with the longitudinal axis of the injector.
  • an annular splitter 44 is mounted on the blades 38 between the outer wall 30 and the sleeve 40.
  • the splitter 44 has a downstream end region which is curved inwardly.
  • the outer surface of the inner wall 24 is also cylindrical with its longitudinal axis coincident with that of the fuel injector. However, as can be seen from Fig. 1, the outer surface of the inner wall 24 does not extend as far downstream as the inner surface of the outer wall 30, but nevertheless terminates adjacent to the outlet end 18 of the body 12.
  • the outwardly flared inner surface 26 lies on substantially the same frustconical surface as the flared end 34 of the outer annular wall 30.
  • the annular fuel passage 32 has a closed upstream end defined by a curved internal surface region of outer wall 30.
  • a series of four discrete fuel discharge holes 46 in the form of bores are provided through part of the inner annular wall 24, although a larger or smaller number of holes 46 may be provided. These holes 46 extend in a common plane which is perpendicular to the longitudinal axis of the fuel injector. However, within such plane, the holes 46 are skewed (as shown in Fig. 2) so as to discharge against regions of the outer cylindrical surface of the fuel passage 32 which lie in such plane, but nevertheless impart a swirl to fuel discharge onto such surface.
  • the holes 46 communicate at their inner ends with a common chamber 48 in the inner wall 24 fed with fuel in use by groove 50 and bore 52 in arm 14.
  • liquid fuel is passed through bore 52 and groove 50 into common chamber 48 from where it passes through the holes 46 so as to have a swirl imparted thereto before being discharged outwardly against the cylindrical outer surface of the annular fuel passage 32.
  • This action is very effective in producing a thin film of liquid fuel which progresses in a helical fashion along the outer surface of the annular fuel passage 32 towards the outlet end 18.
  • air entering the inlet 16 has a swirl imparted thereto by blades 22 and travels along the passage 28.
  • the outer swirling airstream and the inner swirling airstream impinge against the liquid fuel substantially simultaneously and thereby promotes very efficient atomization of the liquid fuel into very fine droplets which are carried into the combustor and burnt efficiently therein.
  • the splitter 44 serves to impart a slight inward movement of part of the air passing through the outer air passage 36 so as to enhance further the interaction between the outer swirling air and the fuel.
  • the outer surface of annular fuel passage 132 converges slightly so as to be of frusto-conical form rather than cylindrical form, with the frusto-conical surface converging in the direction of outlet end 118.
  • the outer surface of outer annular wall 130 curves slightly inwardly so that downstream end 134 of wall 130 is defined by an annular line rather than a frusto-conical surface.
  • the end 134 lies a short distance downstream of the downstream end of inner annular wall 124.
  • the continuation of inner surface 126 of wall 124 intersects the inner surface of wall 130 at a location which is just upstream of end 134.
  • Fuel discharge holes 146 are not only skewed as shown in Fig. 4 to impart a swirl to the fuel passing therethrough, but are also inclined outwardly in the upstream direction (see Fig. 3) so as to discharge fuel against the curved upstream end of annular fuel passage 132.
  • Inner surface 142 of outer annular sleeve 140 is frusto-conical rather than cylindrical and tapers inwardly in the downstream direction. These changes are designed to promote an even more effective atomization of fuel and to reduce even further the risk of carbon building up as a result of decomposition or "cracking" of the fuel under the extreme temperatures experienced in the combustor in service.
  • an upstream region of the surface 142 is cylindrical (like surface 42) whilst the remaining downstream region tapers inwardly.
  • the air flows have a swirl imparted thereto which is in the same direction as that imparted to the fuel.
  • it is within the scope of the invention to arrange for the air flows to have a swirl imparted thereto which is in the opposite direction to that imparted to the fuel If desired, the flow splitter 44 or 144 may be omitted.
  • the injectors described above produce a conical air/fuel stream which is very stable and shows no tendency to flicker or oscillate, and produce very fine droplets.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
EP91301296A 1990-03-02 1991-02-19 Brennstoffeinspritzvorrichtung Withdrawn EP0444811A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9004734 1990-03-02
GB909004734A GB9004734D0 (en) 1990-03-02 1990-03-02 Fuel injector

Publications (1)

Publication Number Publication Date
EP0444811A1 true EP0444811A1 (de) 1991-09-04

Family

ID=10671916

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91301296A Withdrawn EP0444811A1 (de) 1990-03-02 1991-02-19 Brennstoffeinspritzvorrichtung

Country Status (2)

Country Link
EP (1) EP0444811A1 (de)
GB (1) GB9004734D0 (de)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2249118C2 (ru) * 2003-05-23 2005-03-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Низконапорная форсунка и способ распыла топлива
DE10205573B4 (de) * 2002-02-11 2005-10-06 J. Eberspächer GmbH & Co. KG Zerstäuberdüse für einen Brenner
RU2348823C2 (ru) * 2007-04-12 2009-03-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Способ распыливания жидкого углеводородного топлива и форсунка для распыливания
RU2372557C1 (ru) * 2008-06-02 2009-11-10 Владимир Данилович Ковалев Низконапорная форсунка и способ распыла топлива
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20160084503A1 (en) * 2014-09-24 2016-03-24 Pratt & Whitney Canada Corp. Fuel nozzle
EP2385306A3 (de) * 2010-05-07 2017-07-26 Rolls-Royce Deutschland Ltd & Co KG Magervormischbrenner eines Gasturbinentriebwerks mit Strömungsleitelement

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3980233A (en) * 1974-10-07 1976-09-14 Parker-Hannifin Corporation Air-atomizing fuel nozzle
US4170108A (en) * 1975-04-25 1979-10-09 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4216652A (en) * 1978-06-08 1980-08-12 General Motors Corporation Integrated, replaceable combustor swirler and fuel injector
US4373325A (en) * 1980-03-07 1983-02-15 International Harvester Company Combustors

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3980233A (en) * 1974-10-07 1976-09-14 Parker-Hannifin Corporation Air-atomizing fuel nozzle
US4170108A (en) * 1975-04-25 1979-10-09 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4216652A (en) * 1978-06-08 1980-08-12 General Motors Corporation Integrated, replaceable combustor swirler and fuel injector
US4373325A (en) * 1980-03-07 1983-02-15 International Harvester Company Combustors

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10205573B4 (de) * 2002-02-11 2005-10-06 J. Eberspächer GmbH & Co. KG Zerstäuberdüse für einen Brenner
RU2249118C2 (ru) * 2003-05-23 2005-03-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Низконапорная форсунка и способ распыла топлива
RU2348823C2 (ru) * 2007-04-12 2009-03-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Способ распыливания жидкого углеводородного топлива и форсунка для распыливания
RU2372557C1 (ru) * 2008-06-02 2009-11-10 Владимир Данилович Ковалев Низконапорная форсунка и способ распыла топлива
EP2385306A3 (de) * 2010-05-07 2017-07-26 Rolls-Royce Deutschland Ltd & Co KG Magervormischbrenner eines Gasturbinentriebwerks mit Strömungsleitelement
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20160084503A1 (en) * 2014-09-24 2016-03-24 Pratt & Whitney Canada Corp. Fuel nozzle
US9822980B2 (en) * 2014-09-24 2017-11-21 Pratt & Whitney Canada Corp. Fuel nozzle
US10364988B2 (en) 2014-09-24 2019-07-30 Pratt & Whitney Canada Corp. Fuel nozzle

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Publication number Publication date
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