US3608831A - Liquid atomizing devices - Google Patents

Liquid atomizing devices Download PDF

Info

Publication number
US3608831A
US3608831A US839902A US3608831DA US3608831A US 3608831 A US3608831 A US 3608831A US 839902 A US839902 A US 839902A US 3608831D A US3608831D A US 3608831DA US 3608831 A US3608831 A US 3608831A
Authority
US
United States
Prior art keywords
passage
holes
liquid atomizing
liquid
atomizing device
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 - Lifetime
Application number
US839902A
Inventor
Harold Place
Alan G Cheshire
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries 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 Lucas Industries Ltd filed Critical Lucas Industries Ltd
Application granted granted Critical
Publication of US3608831A publication Critical patent/US3608831A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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

Definitions

  • the invention relates to liquid atomizing devices, particularly intended for use in the burners of gas turbine engines.
  • a device comprises a tubular body, through which, in use, air flows to a swirler formed by vanes at the downstream end of the body.
  • the body is mounted on a support which contains a fluid passage communicating with a similar passage within the body.
  • the fluid passage within the body is defined by a tubular member within the body and the passage may lie either within this member or between the member and the body wall.
  • the fluid passage within the body terminates in an end wall within which, or adjacent to which, are a plurality of holes through which fluid is ejected downstream of the swirler and in a direction generally transverse to the airflow.
  • the transverse direction of fluid ejection is achieved either by the directions of the holes themselves or by directing the fluid against a projection of the end wall or of the body.
  • the tubular member may form part of the body or may conveniently be in the form of a cast insert. Preferably there are the same number of holes and vanes, and each hole is adjacent the root of an associated blade at the trailing edge thereof.
  • a liquid atomizing device in accordance with the invention comprises a tubular body through which, in use, air is caused to flow, an air swirler within the downstream end of said body and nozzle means arranged to inject liquid for atomization into the swirling airstream downstream of said swirler in a direction transverse to the airflow.
  • FIGS. I to 7 are views, partially in longitudinal cross section, of six examples of the invention, FIGS. I, 3 and 4L being on a larger scale than the remainder, and FIG. 3 is a section on the line 33 in FIG. 4.
  • the liquid atomizing device shown includes a tubular body of composite construction.
  • the body is supported at one end by a support II through which there extends a liquid supply passage I2.
  • a support II through which there extends a liquid supply passage I2.
  • an air swirler 13 inside the tubular body to create a conically expanding airflow pattern immediately downstream of the body 10.
  • the liquid supply passage 12 is connected to one end of a tube I4 extending coaxially with the tubular body at the downstream end thereof but being bent at the opposite end to join said liquid supply passage.
  • the tube 14b is connected to a hollow centerpiece 15 fitted inside the swirler I3.
  • the centerpiece I5 has a closed wall at one end and adjacent this wall is formed with a series of liquid nozzles 16 through which liquid is ejected in use into the swirling airstream immediately downstream of the swirler 13.
  • nozzles I6 there are the same number of nozzles I6 as there are inclined blades on the swirler I3 and the nozzles 16 are associated respectively with the trailing edges of these blades, each nozzle being arranged adjacent the root of the associated blade, the trailing edge thereof being inclined to the radius along which liquid is ejected by the associated nozzle 16.
  • FIG. 2 The arrangement shown in FIG. 2 is similar to that shown in FIG. I but instead of utilizing the radial nozzles I6 in a centerpiece 15 the tube M is fitted with a different centerpiece I7 incorporating a flange 13 onto which the liquid is directed by the inclined nozzles I9.
  • the airflow through the tubular body I0 breaks up this expanding sheet substantially immediately after it has left the edge of the flange 13.
  • the device shown in FIG. 3 is similar in principle to that shown in FIG. I but is constructed in a different manner.
  • the principal difference is that the tube I I is replaced by a cast insert 20 having a ring portion 21 at its upstream end joined to the central tube 22 by radial arms 23 through which liquid passages 24 extend.
  • FIGS. I and 8 The arrangement shown in FIGS. I and 8 is generally similar to that shown in FIG. 3, but has a cast insert 40 which includes a single liquid passage 41.
  • the passage 41 lies within a radial arm 42 which has a diametrally opposed supporting web 43.
  • the endpiece 15 is secured by welding to the insert I0.
  • Each of the nozzles 16 is adjacent the root of a blade of the swirler I3 at the trailing edge thereof.
  • FIG. 5 there is no central tube M or central cast insert 26.
  • the body is constructed from inner and outer sleeves 25, 26 respectively, defining between them an annular passage 27 communicating with the liquid supply passage 12.
  • This passage 27 terminates at an annular end wall 28 in which axially extending nozzles 29 are formed.
  • the downstream end of the body has an inwardly directed annular rib 30 onto which liquid ejected by the nozzles 29 impinges before being carried away by the swirling airflow downstream of the swirler 13.
  • annular passage 27 terminates in noules 35 arranged around the periphery of the downstream end of the body and directed inwardly across the swirler 13.
  • Each nozzle is, in fact, arranged to produce a jet of liquid which will intersect the axis but which is inclined thereto.
  • a liquid atomizing device comprising a tubular body through which, in use, air is caused to flow, an air swirler within the downstream end of the body and formed of a plurality of blades, a passage within the body for a liquid and nozzle means comprising a plurality of holes communicating with the said passage and arranged to inject liquid for atomization into the airstream downstream of the said swirler in a direction transverse to the airflow, each said hole being adjacent the root of an associated blade and being directed radially from the axis of the said body.
  • a liquid atomizing device as claimed in claim 1 in which the trailing edge of each blade is inclined to the normal to said axis.
  • a liquid atomizing device as claimed in claim I in which the tubular body is of composite construction and includes a transverse portion which acts as a support, the said passage extending through said transverse portion.
  • a liquid atomizing device as claimed in claim 3 in which said passage is defined by a tubular member which is for at least part of its length coaxial with said body.
  • a liquid atomizing device as claimed in claim 4 in which said passage is within the tubular member and said holes are formed adjacent an end wall of the passage.
  • a liquid atomizing device as claimed in claim 5 in which the axes of said holes are substantially perpendicular to the axis of the body.
  • a liquid atomizing device as claimed in claim 4 in which said passage is defined between the tubular member and the body and said holes are formed adjacent an end wall of the passage.
  • a liquid atomizing device as claimed in claim 7 in which the axes of said holes are inclined to the normal to the axis of the body.

Abstract

The invention relates to liquid atomizing devices, particularly intended for use in the burners of gas turbine engines. Such a device comprises a tubular body, through which, in use, air flows to a swirler formed by vanes at the downstream end of the body. The body is mounted on a support which contains a fluid passage communicating with a similar passage within the body. The fluid passage within the body is defined by a tubular member within the body and the passage may lie either within this member or between the member and the body wall. The fluid passage within the body terminates in an end wall within which, or adjacent to which, are a plurality of holes through which fluid is ejected downstream of the swirler and in a direction generally transverse to the airflow. The transverse direction of fluid ejection is achieved either by the directions of the holes themselves or by directing the fluid against a projection of the end wall or of the body. The tubular member may form part of the body or may conveniently be in the form of a cast insert. Preferably there are the same number of holes and vanes, and each hole is adjacent the root of an associated blade at the trailing edge thereof.

Description

llnite States Patent [72] Inventors li-llarold Place Accringtnn; Alan G. Chwhire, hnrnley, both oil England [21] Appl. No. 839,902 [22] Filed July 6, 11969 [45] Patented Sept. 2%, 119711 [73] Assignee ,lnaeph Lucas (industries) Limited Birmingham, England [32] Priority July 18, 11963 [3 3] Great Britain [31] 34308/60 [54] LlQlUm ATOMKZIING DEVICES 8 Claims, 6 Drawing Figs.
[52] US. til 239/406, 239/418 [51] int. Cl B05b 7/10 [50] Field oi Search 239/399, 403, 405, 406, 418
[56] llteierencer Cited UNiTED STATES PATENTS 2,676,648 4/1954 Dennis et a]. 239/406 2,753,929 7/1956 Walshin 239/406 X 3,007,515 11/1961 Furdock 239/406 3,254,846 6/1966 Schreter et al.. 239/406 X 3,493,180 2/1970 Walsh ABSTRACT: The invention relates to liquid atomizing devices, particularly intended for use in the burners of gas turbine engines. Such a device comprises a tubular body, through which, in use, air flows to a swirler formed by vanes at the downstream end of the body. The body is mounted on a support which contains a fluid passage communicating with a similar passage within the body. The fluid passage within the body is defined by a tubular member within the body and the passage may lie either within this member or between the member and the body wall. The fluid passage within the body terminates in an end wall within which, or adjacent to which, are a plurality of holes through which fluid is ejected downstream of the swirler and in a direction generally transverse to the airflow. The transverse direction of fluid ejection is achieved either by the directions of the holes themselves or by directing the fluid against a projection of the end wall or of the body. The tubular member may form part of the body or may conveniently be in the form of a cast insert. Preferably there are the same number of holes and vanes, and each hole is adjacent the root of an associated blade at the trailing edge thereof.
SHEET 10F 5 3 6018 831 mama Sim 1971 PATENTEU SEP'28 lam SHEET W 0F 5 I I I /Y///////////////J N m an 3 km a wm 8% @w ATTOEN EYS LIQUID ATOMIZING DEVICES This invention relates to liquid atomizing devices particularly intended for use in the burners of gas turbine engines.
A liquid atomizing device in accordance with the invention comprises a tubular body through which, in use, air is caused to flow, an air swirler within the downstream end of said body and nozzle means arranged to inject liquid for atomization into the swirling airstream downstream of said swirler in a direction transverse to the airflow.
In the accompanying drawings FIGS. I to 7 are views, partially in longitudinal cross section, of six examples of the invention, FIGS. I, 3 and 4L being on a larger scale than the remainder, and FIG. 3 is a section on the line 33 in FIG. 4.
Referring firstly to the example of the invention shown in FIG. I the liquid atomizing device shown includes a tubular body of composite construction. The body is supported at one end by a support II through which there extends a liquid supply passage I2. At the other end of the body there is an air swirler 13 inside the tubular body to create a conically expanding airflow pattern immediately downstream of the body 10.
The liquid supply passage 12 is connected to one end of a tube I4 extending coaxially with the tubular body at the downstream end thereof but being bent at the opposite end to join said liquid supply passage. The tube 14b is connected to a hollow centerpiece 15 fitted inside the swirler I3. The centerpiece I5 has a closed wall at one end and adjacent this wall is formed with a series of liquid nozzles 16 through which liquid is ejected in use into the swirling airstream immediately downstream of the swirler 13. There are the same number of nozzles I6 as there are inclined blades on the swirler I3 and the nozzles 16 are associated respectively with the trailing edges of these blades, each nozzle being arranged adjacent the root of the associated blade, the trailing edge thereof being inclined to the radius along which liquid is ejected by the associated nozzle 16.
The arrangement shown in FIG. 2 is similar to that shown in FIG. I but instead of utilizing the radial nozzles I6 in a centerpiece 15 the tube M is fitted with a different centerpiece I7 incorporating a flange 13 onto which the liquid is directed by the inclined nozzles I9. The upstream face of the flange I6, which is of greater external diameter than the root diameter of the blades of the swirler I3, is of concave annular form arranged so that liquid impinging upon the concave annular face of the flange I3 is directed therefrom in an expanding sheet in a slightly upstream direction. In use, of course, the airflow through the tubular body I0 breaks up this expanding sheet substantially immediately after it has left the edge of the flange 13.
The device shown in FIG. 3 is similar in principle to that shown in FIG. I but is constructed in a different manner. The principal difference is that the tube I I is replaced by a cast insert 20 having a ring portion 21 at its upstream end joined to the central tube 22 by radial arms 23 through which liquid passages 24 extend.
The arrangement shown in FIGS. I and 8 is generally similar to that shown in FIG. 3, but has a cast insert 40 which includes a single liquid passage 41. The passage 41 lies within a radial arm 42 which has a diametrally opposed supporting web 43. The endpiece 15 is secured by welding to the insert I0. Each of the nozzles 16 is adjacent the root of a blade of the swirler I3 at the trailing edge thereof.
In the example shown in FIG. 5 there is no central tube M or central cast insert 26. Instead the body is constructed from inner and outer sleeves 25, 26 respectively, defining between them an annular passage 27 communicating with the liquid supply passage 12. This passage 27 terminates at an annular end wall 28 in which axially extending nozzles 29 are formed. The downstream end of the body has an inwardly directed annular rib 30 onto which liquid ejected by the nozzles 29 impinges before being carried away by the swirling airflow downstream of the swirler 13.
In the arrangement shown in FIG. 6 the swirler 33 is enclosed within a convergent nozzle 341, but the arrangement is otherwise the same as that shown in FIG. 5.
Turning finally to FIG. 7 the annular passage 27 terminates in noules 35 arranged around the periphery of the downstream end of the body and directed inwardly across the swirler 13. Each nozzle is, in fact, arranged to produce a jet of liquid which will intersect the axis but which is inclined thereto.
All the above-described devices are intended to give proper atomization of liquid over a wide range of liquid pressures and airflow rates. This is of particular importance in the burners of gas turbine engines since very low fuel pressures and airflow rates are available during starting, but the same burners are required to operate efficiently at high pressures and high airflow rates during high speed running of the engine.
Having thus described our invention what we claim as new and desire to secure by Letters Patent. is:
I. A liquid atomizing device comprising a tubular body through which, in use, air is caused to flow, an air swirler within the downstream end of the body and formed of a plurality of blades, a passage within the body for a liquid and nozzle means comprising a plurality of holes communicating with the said passage and arranged to inject liquid for atomization into the airstream downstream of the said swirler in a direction transverse to the airflow, each said hole being adjacent the root of an associated blade and being directed radially from the axis of the said body.
2. A liquid atomizing device as claimed in claim 1 in which the trailing edge of each blade is inclined to the normal to said axis.
3. A liquid atomizing device as claimed in claim I in which the tubular body is of composite construction and includes a transverse portion which acts as a support, the said passage extending through said transverse portion.
4!. A liquid atomizing device as claimed in claim 3 in which said passage is defined by a tubular member which is for at least part of its length coaxial with said body.
5. A liquid atomizing device as claimed in claim 4 in which said passage is within the tubular member and said holes are formed adjacent an end wall of the passage.
6. A liquid atomizing device as claimed in claim 5 in which the axes of said holes are substantially perpendicular to the axis of the body.
7. A liquid atomizing device as claimed in claim 4 in which said passage is defined between the tubular member and the body and said holes are formed adjacent an end wall of the passage.
8. A liquid atomizing device as claimed in claim 7 in which the axes of said holes are inclined to the normal to the axis of the body.

Claims (8)

1. A liquid atomizing device comprising a tubular body through which, in use, air is caused to flow, an air swirler within the downstream end of the body and formed of a plurality of blades, a passage within the body for a liquid and nozzle means comprising a plurality of holes communicating with the said passage and arranged to inject liquid for atomization into the airstream downstream of the said swirler in a direction transverse to the airflow, each said hole being adjacent the root of an associated blade and being directed radially from the axis of the said body.
2. A liquid atomizing device as claimed in claim 1 in which the trailing edge of each blade is inclined to the normal to said axis.
3. A liquid atomizing device as claimed in claim 1 in which the tubular body is of composite construction and includes a transverse portion which acts as a support, the said passage extending through said transverse portion.
4. A liquid atomizing device as claimed in claim 3 in which said passage is defined by a tubular member which is for at least part of its length coaxial with said body.
5. A liquid atomizing device as claimed in claim 4 in which said passage is within the tubular member and said holes are formed adjacent an end wall of the passage.
6. A liquid atomizing device as claimed in claim 5 in which the axes of said holes are substantially perpendicular to the axis of the body.
7. A liquid atomizing device as claimed in claim 4 in which said passage is defined between the tubular member and the body and said holes are formed adjacent an end wall of the passage.
8. A liquid atomizing device as claimed in claim 7 in which the axes of said holes are inclined to the normal to the axis of the body.
US839902A 1968-07-18 1969-07-08 Liquid atomizing devices Expired - Lifetime US3608831A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB34308/68A GB1275255A (en) 1968-07-18 1968-07-18 Liquid atomising devices

Publications (1)

Publication Number Publication Date
US3608831A true US3608831A (en) 1971-09-28

Family

ID=10364022

Family Applications (1)

Application Number Title Priority Date Filing Date
US839902A Expired - Lifetime US3608831A (en) 1968-07-18 1969-07-08 Liquid atomizing devices

Country Status (6)

Country Link
US (1) US3608831A (en)
JP (1) JPS4825445B1 (en)
DE (2) DE1966554A1 (en)
FR (1) FR2014640A1 (en)
GB (1) GB1275255A (en)
SE (3) SE377827B (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3904119A (en) * 1973-12-05 1975-09-09 Avco Corp Air-fuel spray nozzle
US3927835A (en) * 1973-11-05 1975-12-23 Lucas Aerospace Ltd Liquid atomising devices
US3975141A (en) * 1974-06-25 1976-08-17 The United States Of America As Represented By The Secretary Of The Army Combustion liner swirler
US4364522A (en) * 1980-07-21 1982-12-21 General Motors Corporation High intensity air blast fuel nozzle
US4646968A (en) * 1985-04-17 1987-03-03 The Dow Chemical Company Prilling apparatus
US5009589A (en) * 1989-12-08 1991-04-23 Sundstrand Corporation Stored energy combustor fuel injection system
US5873237A (en) * 1997-01-24 1999-02-23 Westinghouse Electric Corporation Atomizing dual fuel nozzle for a combustion turbine
US6082111A (en) * 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
US20030084667A1 (en) * 2001-11-05 2003-05-08 Miklos Gerendas Device for the injection of fuel into the flow wake of swirler vanes
FR2875584A1 (en) * 2004-09-23 2006-03-24 Snecma Moteurs Sa EFFERVESCENCE INJECTOR FOR AEROMECHANICAL AIR / FUEL INJECTION SYSTEM IN A TURBOMACHINE COMBUSTION CHAMBER
US20090139240A1 (en) * 2007-09-13 2009-06-04 Leif Rackwitz Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
US20120137695A1 (en) * 2010-12-01 2012-06-07 General Electric Company Fuel nozzle with gas only insert
US20140237875A1 (en) * 2013-02-26 2014-08-28 Richard A. Randall Card Display Unit System
RU170359U1 (en) * 2016-10-05 2017-04-24 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Injector module of a low-emission combustion chamber of a gas turbine engine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1586866A (en) * 1976-11-11 1981-03-25 Lucas Industries Ltd Liquid fuel atomiser assemlby
FR2508602B1 (en) * 1981-06-29 1986-03-21 Cherny Anatoly PROCESS FOR DELIVERING FUEL INTO THE OXIDIZING MEDIUM DURING COMBUSTION AND DEVICE FOR CARRYING OUT IT
GB2129710B (en) * 1982-10-27 1986-04-23 Cabot Corp Carbon black burner
FR2695713B1 (en) * 1992-09-17 1994-10-21 Snecma Aerodynamic premix injection system.
FR3009687B1 (en) * 2013-08-13 2017-05-12 Sames Tech LUBRICATING SPRAYER AND LUBRICATING PLANT COMPRISING THE SPRAYER
CN105214866A (en) * 2015-08-13 2016-01-06 刘昊源 A kind of air-assisted sprayer

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2676648A (en) * 1952-01-29 1954-04-27 Boston Machine Works Co Adjustable head for oil burners
US2753929A (en) * 1951-12-27 1956-07-10 Silent Flame Mfg Co Inc Oil burner
US3007515A (en) * 1955-11-14 1961-11-07 John M Furdock Oil burners
US3254846A (en) * 1965-01-21 1966-06-07 Hauck Mfg Co Oil atomizing burner using low pressure air
US3493180A (en) * 1968-11-06 1970-02-03 Gulf Research Development Co Oil burner combustion head swirl means

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2753929A (en) * 1951-12-27 1956-07-10 Silent Flame Mfg Co Inc Oil burner
US2676648A (en) * 1952-01-29 1954-04-27 Boston Machine Works Co Adjustable head for oil burners
US3007515A (en) * 1955-11-14 1961-11-07 John M Furdock Oil burners
US3254846A (en) * 1965-01-21 1966-06-07 Hauck Mfg Co Oil atomizing burner using low pressure air
US3493180A (en) * 1968-11-06 1970-02-03 Gulf Research Development Co Oil burner combustion head swirl means

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3927835A (en) * 1973-11-05 1975-12-23 Lucas Aerospace Ltd Liquid atomising devices
US3904119A (en) * 1973-12-05 1975-09-09 Avco Corp Air-fuel spray nozzle
US3975141A (en) * 1974-06-25 1976-08-17 The United States Of America As Represented By The Secretary Of The Army Combustion liner swirler
US4364522A (en) * 1980-07-21 1982-12-21 General Motors Corporation High intensity air blast fuel nozzle
US4646968A (en) * 1985-04-17 1987-03-03 The Dow Chemical Company Prilling apparatus
US5009589A (en) * 1989-12-08 1991-04-23 Sundstrand Corporation Stored energy combustor fuel injection system
US5873237A (en) * 1997-01-24 1999-02-23 Westinghouse Electric Corporation Atomizing dual fuel nozzle for a combustion turbine
US6082111A (en) * 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
US20030084667A1 (en) * 2001-11-05 2003-05-08 Miklos Gerendas Device for the injection of fuel into the flow wake of swirler vanes
US6901756B2 (en) * 2001-11-05 2005-06-07 Rolls-Royce Deutschland Ltd & Co Kg Device for the injection of fuel into the flow wake of swirler vanes
FR2875584A1 (en) * 2004-09-23 2006-03-24 Snecma Moteurs Sa EFFERVESCENCE INJECTOR FOR AEROMECHANICAL AIR / FUEL INJECTION SYSTEM IN A TURBOMACHINE COMBUSTION CHAMBER
EP1640662A1 (en) * 2004-09-23 2006-03-29 Snecma Effervescent injector for an aeromechanical air/fuel injection system integrated into a gas turbine combustor
US7568345B2 (en) 2004-09-23 2009-08-04 Snecma Effervescence injector for an aero-mechanical system for injecting air/fuel mixture into a turbomachine combustion chamber
US20090139240A1 (en) * 2007-09-13 2009-06-04 Leif Rackwitz Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
US8646275B2 (en) 2007-09-13 2014-02-11 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
US20120137695A1 (en) * 2010-12-01 2012-06-07 General Electric Company Fuel nozzle with gas only insert
US20140237875A1 (en) * 2013-02-26 2014-08-28 Richard A. Randall Card Display Unit System
RU170359U1 (en) * 2016-10-05 2017-04-24 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Injector module of a low-emission combustion chamber of a gas turbine engine

Also Published As

Publication number Publication date
SE351892B (en) 1972-12-11
SE377827B (en) 1975-07-28
DE1966554A1 (en) 1973-03-08
SE377709B (en) 1975-07-21
DE1936416B2 (en) 1977-06-02
FR2014640A1 (en) 1970-04-17
JPS4825445B1 (en) 1973-07-28
DE1936416A1 (en) 1970-01-22
DE1966555A1 (en) 1973-03-08
GB1275255A (en) 1972-05-24

Similar Documents

Publication Publication Date Title
US3608831A (en) Liquid atomizing devices
JP6047222B2 (en) Fuel nozzle structure
US2676460A (en) Burner construction of the can-an-nular type having means for distributing airflow to each can
JP6606080B2 (en) Fuel nozzle structure for air-assisted fuel injection
US2979899A (en) Flame spreading device for combustion equipments
US4862693A (en) Fuel injector for a turbine engine
US3299632A (en) Combustion chamber for a gas turbine engine
JP3882151B2 (en) Method for distributing fuel in a gas turbine engine
CN106247404B (en) Membranae praeformativa air blast (PAB) guiding device with annular splitter
CN106247405B (en) Membranae praeformativa air blast (PAB) guiding device for low emission combustor
US3720058A (en) Combustor and fuel injector
KR930020090A (en) Dual Combustor for Gas Turbines
KR20010085488A (en) Combustor liner cooling thimbles and related method
EP3348908B1 (en) Gas turbine fuel injector
KR101752114B1 (en) Nozzle, combustion apparatus, and gas turbine
US2981066A (en) Turbo machine
US3483699A (en) Fuel injector for a gas turbine engine
JP3826196B2 (en) Pre-filmer type air blast atomization nozzle
JP2008530483A (en) Low cost pressurized atomizer
CN106016364B (en) A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle)
US4290558A (en) Fuel nozzle with water injection
US5241818A (en) Fuel injector for a gas turbine engine
US2714287A (en) Flameholder device for turbojet afterburner
US5027603A (en) Turbine engine with start injector
US3682390A (en) Liquid atomizing devices