US3608831A - Liquid atomizing devices - Google Patents

Liquid atomizing devices Download PDF

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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
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United States
Prior art keywords
passage
holes
liquid atomizing
liquid
atomizing device
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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
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US839902A
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English (en)
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
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Filing date
Publication date
Application filed by Lucas Industries Ltd filed Critical Lucas Industries Ltd
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    • 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.
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

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

Country Status (6)

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US (1) US3608831A (xx)
JP (1) JPS4825445B1 (xx)
DE (2) DE1966554A1 (xx)
FR (1) FR2014640A1 (xx)
GB (1) GB1275255A (xx)
SE (3) SE377709B (xx)

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 (fr) * 2004-09-23 2006-03-24 Snecma Moteurs Sa Injecteur a effervescence pour systeme aeromecanique d'injection air/carburant dans une chambre de combustion de turbomachine
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 (ru) * 2016-10-05 2017-04-24 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Форсуночный модуль малоэмиссионной камеры сгорания газотурбинного двигателя

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 (fr) * 1981-06-29 1986-03-21 Cherny Anatoly Procede d'amenee du combustible dans le milieu oxydant lors de la combustion et dispositif pour sa mise en oeuvre
GB2129710B (en) * 1982-10-27 1986-04-23 Cabot Corp Carbon black burner
FR2695713B1 (fr) * 1992-09-17 1994-10-21 Snecma Système d'injection aérodynamique à prémélange.
FR3009687B1 (fr) * 2013-08-13 2017-05-12 Sames Tech Pulverisateur d'un produit lubrifiant et installation de lubrification comprenant ce pulverisateur
CN105214866A (zh) * 2015-08-13 2016-01-06 刘昊源 一种风送喷雾机

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 (fr) * 2004-09-23 2006-03-24 Snecma Moteurs Sa Injecteur a effervescence pour systeme aeromecanique d'injection air/carburant dans une chambre de combustion de turbomachine
EP1640662A1 (fr) * 2004-09-23 2006-03-29 Snecma Injecteur à effervescence pour système aéromécanique d'injection air/carburant dans une chambre de combustion de turbomachine
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 (ru) * 2016-10-05 2017-04-24 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Форсуночный модуль малоэмиссионной камеры сгорания газотурбинного двигателя

Also Published As

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

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