US3662959A - Fuel injection nozzle - Google Patents

Fuel injection nozzle Download PDF

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US3662959A
US3662959A US61969A US3662959DA US3662959A US 3662959 A US3662959 A US 3662959A US 61969 A US61969 A US 61969A US 3662959D A US3662959D A US 3662959DA US 3662959 A US3662959 A US 3662959A
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Prior art keywords
fuel
tube
housing
primary
injection nozzle
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US61969A
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Harry Sample Jr
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Parker Intangibles LLC
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Parker Hannifin Corp
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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F23D11/26—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed

Definitions

  • a fuel injection nozzle of the dual orifice type characterized in that the elongated primary fuel passage in the nonle housing is constituted by a length of tube which is thermally isolated from the housing whereby the flow of fuel through the tube maintains the interior wall thereof at a temperature below that at which carbonizing of the fuel would occur.
  • Dual orifice fuel injection nozzles for gas turbines and the like generally comprise an elongated housing having a fuel inlet port and flow divider at one end and a spray noule at the other end, said one end being flanged for mounting as on the wall of the combustion chamber. Between the fuel inlet port and flow divider and the spray nozzle the housing is provided with elongated primary and secondary passages which respectively communicate with the fuel inlet port upstream and downstream of the flow divider and lead to the primary and secondary discharge orifices of the noule. As shown, for example, in the US. Pat. to Cleminshaw et al. No. 3,154,095, granted Oct.
  • the intermediate portion of the housing is defined by elongated primary and secondary tubes which extend alongside each other and which are brazed at their ends to the flow divider body and to the nozzle body.
  • the nozzle housing is of unitary form, a forging for example, in which the elongated secondary passage is in the form of a drilled hole, and the primary passage is the bore of a primary tube which extends in spaced relation through the secondary passage and which has its ends brazed in place to communicate with a fuel inlet port which is upstream of the secondary flow control valve and with the primary discharge orifice.
  • the interior wall of the primary tube may become overheated owing to the limited cooling rate of the low primary flow rate thus to permit carbonizing of the fuel with consequent flaking or breaking off of such carbon deposits and resultant plugging of the primary discharge orifice and/or the primary swirl passages.
  • a heat shield is disposed around the primary and secondary tubes, as aforesaid, the air space around said tubes may become highly heated so that the low primary fuel flow rate may not be able to maintain the wall of the primary passage below fuel carbonizing temperature.
  • the tubes are in good heat conducting relation with the nozzle housing where their ends are brazed in place.
  • the nozzle of US, Pat. No. 3,029,029 may be satisfactory insofar as maintaining the temperature of the wall of the passage in the primary tube at less than fuel carbonizing temperature because of the cooling effect of the secondary fuel flow therearound, and the cooling effect of the primary fuel flow through the primary tube.
  • the location and shape of the primary tube entails difficult and expensive assembly operations in view of the angular construction of the nozzle end of the housing with insertion thereinto, prior to brazing of the primary tube, of a nozzle insert containing both the primary and secondary passages whereby brazing of that end of the primary tube to the insert is difficult, and moreover, the other end of the primary tube is bent to fit into an angular passage in the housing.
  • FIG. 1 is a side elevation view of a dual orifice fuel injection nozzle embodying the present invention
  • FIG. 2 is an enlarged fragmentary cross-section view showing the elongated primary tube which is thermally insulated from the nozzle housing;
  • FIG. 3 is a fragmentary cross-section view similar to FIG. 2 except illustrating a modification in the primary tube.
  • the fuel injection nozzle herein comprises a housing and nozzle assembly lhaving a fuel inlet port 2 at one end of the housing 3, a dual orifice injection noule 4 at the other end, and a mounting flange 5 between the ends for mounting the assembly 1 as on the wall of a combustion chamber of a gas turbine or the like.
  • a flow divider or variable area valve 6 which controls the flow of fuel from the fuel inlet port 2 to the secondary discharge orifice (not shown) of the nozzle 4 via the elongated secondary passage 7 downstream of the flow divider 6.
  • the flow divider 6 comprises a sleeve 8 which is held in place by the hold-down spring 9 and which provides a seat 10 for the spring biased valve spool 11, the valve spool 11 having one or more metering slots 12 to control the flow of secondary fuel to the nozzle 4 as the valve spool 11 is urged downwardly by fuel pressure overcoming the bias of the spring 13 acting on the valve spool 11.
  • the housing 3 is provided with an elongated drilled hole 14 which, adjacent its lower end, has a stop shoulder 15.
  • a metallic primary tube 16 Disposed in said hole 14 is a metallic primary tube 16 which is, for example, of 0.001 to 0.006 inch smaller diameter than the diameter of the drilled hole 14, the lower end of the tube 16 being engaged with the shoulder 15 and the upper end of the tube 16 extending up into a slot 17 in the flange of the flow divider sleeve 8.
  • the lower end of the hold-down spring 9 radially overlaps the upper end of the tube 16 to limit axial movement of the latter.
  • the upper open end of the tube 16 communicates with the fuel inlet port 2 upstream of the flow divider 6 so that the nozzle 4 will be supplied with primaryfuel through the tube 16 whether the flow divider 6 is in closed or open position.
  • a heat shield 18 Surrounding the housing 3 is a heat shield 18 to form an air space to decrease heat transmission from the combustion chamber to the housing 3.
  • the flow of fuel through the primary orifice may only be lbs/hr. whereas the flow of fuel through the secondary orifice may be 600 lbs/hr. Accordingly, generally no problem of carbonizing of fuel on the wall of the elongated secondary passage 7 is encountered in view of the relatively great cooling capacity of the secondary flow. However, because the primary flow is of such low magnitude, the wall of the elongated passage 14 is apt to reach a temperature, of say, 600 R, which would cause carbonimng of the fuel on the wall with consequent flaking or breaking off of the carbon deposits with consequent danger of plugging of the primary discharge orifice.
  • the primary flow is through the elongated metallic tube 16 which is insulated from the housing passage 16 by reason of the loose fit of the tube 16 in the drilled hole 14 in the housing3.
  • the tube 16 and housing 3 There is no region of good heat transfer contact between the tube 16 and housing 3 whereby, even through the primary flow rate is of low magnitude, it will nevertheless be sufficient to cool the primary tube 16 to maintain its interior wall temperature less than that which will cause carbonizing of the fuel.
  • the primary insulating tube 19 has a flared or flanged upper end 20, the hold-down spring 21 for the flow divider sleeve 22 radially overlapping the upper end 20 of said tube 19 to prevent axial displacement thereof.
  • the primary tube 16 or 19 is loosely disposed in a bore 14 in the housing 3 so that it is thermally isolated from the housing 3. Furthermore, it is preferred that the upper end of the primary tube 16 or 19 be axially spaced from the hold-down spring 9 or 21 to avoid firm contact of the lower end of tube 16 with the stop shoulder 15 or of the flange 20 of tube 19 with the housing 3. In the example herein, (tube 16 or 19 of 0.001 to 0.006 in. diameter smaller than bore 16) the tube 16 or 19 is effectively thermally insulated from the housing 3 and substantially the entire primary fuel flow contacts the interior wall of the tube 16 or 19 to cool it below fuel-carbonizing temperature.
  • a dual orifice fuel injection nozzle assembly wherein an elongated housing has primary and secondary fuel supply passages therein leading to the respective primary and secondary discharge orifices of a dual orifice nozzle at one end of said housing operative to spray fuel into the combustion chamber of a gas turbine or the like
  • the improvement which comprises an elongated open ended metallic tube loosely disposed in a bore in said housing and constituting a substantial portion of the length of the primary fuel supply passage; said tube being thus thermally isolated from said housing whereby primary fuel flowing through said tube cools the interior wall thereof to prevent carbonizing of the fuel flowing in contact therewith.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

A fuel injection nozzle of the dual orifice type characterized in that the elongated primary fuel passage in the nozzle housing is constituted by a length of tube which is thermally isolated from the housing whereby the flow of fuel through the tube maintains the interior wall thereof at a temperature below that at which carbonizing of the fuel would occur.

Description

United States Patent Sample, Jr.
[52] U.S.Cl. ..239/533 [51] lnt.Cl.... ..B05b 1/30 [58] Field ofSearch ..l37/469, 54l;239/533, 401; 60/3974 [56] References Cited UN lTED STATES PATENTS 2,959,360 1 1/1960 Nichols ..239/533 [451 May 16, 1972 2,592,111 4/1952 Bischof ..239/533 3,029,029 4/1962 Webster 3,131,866 5/1964 Cummins et al ..239/533 3,154,095 10/ 1964 Cleminshaw et al. ..239/410 X 3,379,374 4/1968 Mekkes ....239/533 X 3,387,790 6/1968 De Luca ..239/533 X Primary Examiner-Lloyd L. King Attorney-Oberlin, Maky, Donnelly & Renner ABSTRACT A fuel injection nozzle of the dual orifice type characterized in that the elongated primary fuel passage in the nonle housing is constituted by a length of tube which is thermally isolated from the housing whereby the flow of fuel through the tube maintains the interior wall thereof at a temperature below that at which carbonizing of the fuel would occur.
5 Claim, 3 Drawing Figures Patented May 16, 1972 INVENTOR.
HARRY SAMPLE,JR
B Y JOQZAqWQQ BACKGROUND OF THE INVENTION Dual orifice fuel injection nozzles for gas turbines and the like generally comprise an elongated housing having a fuel inlet port and flow divider at one end and a spray noule at the other end, said one end being flanged for mounting as on the wall of the combustion chamber. Between the fuel inlet port and flow divider and the spray nozzle the housing is provided with elongated primary and secondary passages which respectively communicate with the fuel inlet port upstream and downstream of the flow divider and lead to the primary and secondary discharge orifices of the noule. As shown, for example, in the US. Pat. to Cleminshaw et al. No. 3,154,095, granted Oct. 27, 1964, the intermediate portion of the housing is defined by elongated primary and secondary tubes which extend alongside each other and which are brazed at their ends to the flow divider body and to the nozzle body. Furthermore, in some cases as shown for example in the US. Pats. to Webster et al. No. 3,013,732, granted Dec. 19, 1961, and Moebius et al. No. 3,159,971, granted Dec. 8, 1964, there may be a heat shield around the aforementioned primary and secondary tubes. In another known construction (Webster U.S Pat. No. 3,029,029, granted Apr. 10, 1962), the nozzle housing is of unitary form, a forging for example, in which the elongated secondary passage is in the form of a drilled hole, and the primary passage is the bore of a primary tube which extends in spaced relation through the secondary passage and which has its ends brazed in place to communicate with a fuel inlet port which is upstream of the secondary flow control valve and with the primary discharge orifice.
In the known constructions wherein the primary and secondary tubes are exposed, the interior wall of the primary tube may become overheated owing to the limited cooling rate of the low primary flow rate thus to permit carbonizing of the fuel with consequent flaking or breaking off of such carbon deposits and resultant plugging of the primary discharge orifice and/or the primary swirl passages. Even when a heat shield is disposed around the primary and secondary tubes, as aforesaid, the air space around said tubes may become highly heated so that the low primary fuel flow rate may not be able to maintain the wall of the primary passage below fuel carbonizing temperature. Moreover, the tubes are in good heat conducting relation with the nozzle housing where their ends are brazed in place.
From an operational standpoint, the nozzle of US, Pat. No. 3,029,029 may be satisfactory insofar as maintaining the temperature of the wall of the passage in the primary tube at less than fuel carbonizing temperature because of the cooling effect of the secondary fuel flow therearound, and the cooling effect of the primary fuel flow through the primary tube. However, the location and shape of the primary tube entails difficult and expensive assembly operations in view of the angular construction of the nozzle end of the housing with insertion thereinto, prior to brazing of the primary tube, of a nozzle insert containing both the primary and secondary passages whereby brazing of that end of the primary tube to the insert is difficult, and moreover, the other end of the primary tube is bent to fit into an angular passage in the housing.
SUMMARY OF THE INVENTION primary tube to the point where carbonizing of the fuel would occur.
Other objects and advantages of the present invention will appear hereinafter.
BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is a side elevation view of a dual orifice fuel injection nozzle embodying the present invention;
FIG. 2 is an enlarged fragmentary cross-section view showing the elongated primary tube which is thermally insulated from the nozzle housing; and
FIG. 3 is a fragmentary cross-section view similar to FIG. 2 except illustrating a modification in the primary tube.
DETAILED DESCRIPTION OF THE INVENTION The fuel injection nozzle herein comprises a housing and nozzle assembly lhaving a fuel inlet port 2 at one end of the housing 3, a dual orifice injection noule 4 at the other end, and a mounting flange 5 between the ends for mounting the assembly 1 as on the wall of a combustion chamber of a gas turbine or the like. i
In the intermediate portion of the housing 3 adjacent the flange 5 is a flow divider or variable area valve 6 which controls the flow of fuel from the fuel inlet port 2 to the secondary discharge orifice (not shown) of the nozzle 4 via the elongated secondary passage 7 downstream of the flow divider 6.
As herein shown, the flow divider 6 comprises a sleeve 8 which is held in place by the hold-down spring 9 and which provides a seat 10 for the spring biased valve spool 11, the valve spool 11 having one or more metering slots 12 to control the flow of secondary fuel to the nozzle 4 as the valve spool 11 is urged downwardly by fuel pressure overcoming the bias of the spring 13 acting on the valve spool 11.
Alongside the aforesaid secondary fuel passage 7, the housing 3 is provided with an elongated drilled hole 14 which, adjacent its lower end, has a stop shoulder 15. Disposed in said hole 14 is a metallic primary tube 16 which is, for example, of 0.001 to 0.006 inch smaller diameter than the diameter of the drilled hole 14, the lower end of the tube 16 being engaged with the shoulder 15 and the upper end of the tube 16 extending up into a slot 17 in the flange of the flow divider sleeve 8. The lower end of the hold-down spring 9 radially overlaps the upper end of the tube 16 to limit axial movement of the latter. The upper open end of the tube 16 communicates with the fuel inlet port 2 upstream of the flow divider 6 so that the nozzle 4 will be supplied with primaryfuel through the tube 16 whether the flow divider 6 is in closed or open position.
Surrounding the housing 3 is a heat shield 18 to form an air space to decrease heat transmission from the combustion chamber to the housing 3.
In a typical dual orifice nozzle 4 with an inlet pressure of say, 400 psi, the flow of fuel through the primary orifice (not shown) may only be lbs/hr. whereas the flow of fuel through the secondary orifice may be 600 lbs/hr. Accordingly, generally no problem of carbonizing of fuel on the wall of the elongated secondary passage 7 is encountered in view of the relatively great cooling capacity of the secondary flow. However, because the primary flow is of such low magnitude, the wall of the elongated passage 14 is apt to reach a temperature, of say, 600 R, which would cause carbonimng of the fuel on the wall with consequent flaking or breaking off of the carbon deposits with consequent danger of plugging of the primary discharge orifice.
In the present case, the primary flow is through the elongated metallic tube 16 which is insulated from the housing passage 16 by reason of the loose fit of the tube 16 in the drilled hole 14 in the housing3. There is no region of good heat transfer contact between the tube 16 and housing 3 whereby, even through the primary flow rate is of low magnitude, it will nevertheless be sufficient to cool the primary tube 16 to maintain its interior wall temperature less than that which will cause carbonizing of the fuel.
In the modification illustrated in FIG. 3, instead of the stop shoulder 15 in the drilled hole 14 of the housing 3 shown in FIG. 2, the primary insulating tube 19 has a flared or flanged upper end 20, the hold-down spring 21 for the flow divider sleeve 22 radially overlapping the upper end 20 of said tube 19 to prevent axial displacement thereof.
In summary, it can be seen that the primary tube 16 or 19 is loosely disposed in a bore 14 in the housing 3 so that it is thermally isolated from the housing 3. Furthermore, it is preferred that the upper end of the primary tube 16 or 19 be axially spaced from the hold-down spring 9 or 21 to avoid firm contact of the lower end of tube 16 with the stop shoulder 15 or of the flange 20 of tube 19 with the housing 3. In the example herein, ( tube 16 or 19 of 0.001 to 0.006 in. diameter smaller than bore 16) the tube 16 or 19 is effectively thermally insulated from the housing 3 and substantially the entire primary fuel flow contacts the interior wall of the tube 16 or 19 to cool it below fuel-carbonizing temperature.
I, therefore, particularly point out and distinctly claim as my invention; I
1. In a dual orifice fuel injection nozzle assembly wherein an elongated housing has primary and secondary fuel supply passages therein leading to the respective primary and secondary discharge orifices of a dual orifice nozzle at one end of said housing operative to spray fuel into the combustion chamber of a gas turbine or the like, the improvement which comprises an elongated open ended metallic tube loosely disposed in a bore in said housing and constituting a substantial portion of the length of the primary fuel supply passage; said tube being thus thermally isolated from said housing whereby primary fuel flowing through said tube cools the interior wall thereof to prevent carbonizing of the fuel flowing in contact therewith.
2. The fuel injection nozzle assembly of claim 1, wherein said housing has a flow divider therein for flow of fuel therethrough into said secondary fuel supply passage.
3. The fuel injection noule assembly of claim 1, wherein said housing has means radially overlapping one end of said tube to limit axial movement thereof in said bore.
4. The fuel injection nozzle assembly of claim 3, wherein said bore has a stop shoulder adjacent the other end of said tube.
5. The fuel injection nozzle assembly of claim 3, wherein said one end of said tube, adjacent to the end of said bore, is enlarged to a diameter greater than that of said bore.

Claims (5)

1. In a dual orifice fuel injection nozzle assembly wherein an elongated housing has primary and secondary fuel supply passages therein leading to the respective primary and secondary discharge orifices of a dual orifice nozzle at one end of said housing operative to spray fuel into the combustion chamber of a gas turbine or the like, the improvement which comprises an elongated open ended metallic tube loosely disposed in a bore in said housing and constituting a substantial portion of the length of the primary fuel supply passage; said tube being thus thermally isolated from said housing whereby primary fuel flowing through said tube cools the interior wall thereof to prevent carbonizing of the fuel flowing in contact therewith.
2. The fuel injection nozzle assembly of claim 1, wherein said housing has a flow divider therein for flow of fuel therethrough into said secondary fuel supply passage.
3. The fuel injection nozzle assembly of claim 1, wherein said housing has means radially overlapping one end of said tube to limit axial movement thereof in said bore.
4. The fuel injection nozzle assembly of claim 3, wherein said bore has a stop shoulder adjacent the other end of said tube.
5. The fuel injection nozzle assembly of claim 3, wherein said one end of said tube, adjacent to the end of said bore, is enlarged to a diameter greater than that of said bore.
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Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4111369A (en) * 1977-07-05 1978-09-05 General Motors Corporation Fuel nozzle
US4111365A (en) * 1973-12-26 1978-09-05 Isuzu Motors Limited Fuel injection system and its nozzle holder
FR2471480A1 (en) * 1979-12-13 1981-06-19 Snecma INJECTION DEVICE FOR A COMBUSTION CHAMBER FOR A TURBINE ENGINE
FR2540186A1 (en) * 1983-01-27 1984-08-03 Ex Cell O Corp PRESSURE ATOMIZED FUEL INJECTOR
EP0132213A3 (en) * 1983-07-19 1986-02-12 United Technologies Corporation Fuel nozzle for gas turbine engine
FR2622634A1 (en) * 1987-11-04 1989-05-05 United Technologies Corp FUEL INJECTOR ASSEMBLY FOR AN AXIAL FLOW ROTATING MACHINE AND METHOD OF PROTECTING FUEL ARISING IN A PASSAGE THEREWITH
FR2626043A1 (en) * 1988-01-14 1989-07-21 Gen Electric TURBULENCE-FUEL INJECTOR FORMATION DEVICE FOR A COMBUSTION ASSEMBLY IN A GAS TURBINE
US4938418A (en) * 1988-12-01 1990-07-03 Fuel Systems Textron Inc. Modular fuel nozzle assembly for gas turbine engines
US5269468A (en) * 1992-06-22 1993-12-14 General Electric Company Fuel nozzle
US6141968A (en) * 1997-10-29 2000-11-07 Pratt & Whitney Canada Corp. Fuel nozzle for gas turbine engine with slotted fuel conduits and cover
US6149075A (en) * 1999-09-07 2000-11-21 General Electric Company Methods and apparatus for shielding heat from a fuel nozzle stem of fuel nozzle
US6276141B1 (en) 1996-03-13 2001-08-21 Parker-Hannifin Corporation Internally heatshielded nozzle
EP1312864A1 (en) * 2001-11-20 2003-05-21 Hispano Suiza Dosing device for turbomachine fuel injector
EP1312863A1 (en) * 2001-11-20 2003-05-21 Hispano Suiza Improvements to turbomachine injectors
US20050284956A1 (en) * 2004-06-25 2005-12-29 Mast Ryan J Universal sprinkler housing
US20060054233A1 (en) * 2004-09-15 2006-03-16 Prociw Lev A Flexible heat shields and method
US20070283931A1 (en) * 2006-05-19 2007-12-13 Delavan Inc Apparatus and method to compensate for differential thermal growth of injector components
EP1947310A1 (en) * 2007-01-22 2008-07-23 Hispano-Suiza Two-stage fuel injector
US20100051728A1 (en) * 2008-08-27 2010-03-04 Woodward Governor Company Piloted Variable Area Fuel Injector
US20100071667A1 (en) * 2008-09-19 2010-03-25 Woodward Governor Company Active Thermal Protection For Fuel Injectors
US20100199676A1 (en) * 2009-02-12 2010-08-12 Victor Gandza Fuel delivery system with reduced heat transfer to fuel manifold seal
US20100229555A1 (en) * 2006-03-03 2010-09-16 Pratt & Whitney Canada Corp. Fuel manifold with reduced losses
US20110041805A1 (en) * 2009-08-20 2011-02-24 Delavan Inc System and method for locking retention of valve components
US20110073071A1 (en) * 2009-09-30 2011-03-31 Woodward Governor Company Internally Nested Variable-Area Fuel Nozzle
US20110085895A1 (en) * 2009-10-09 2011-04-14 Pratt & Whitney Canada Corp. Oil tube with integrated heat shield
US20110108639A1 (en) * 2009-11-09 2011-05-12 Woodward Governor Company Variable-Area Fuel Injector With Improved Circumferential Spray Uniformity
WO2012075078A3 (en) * 2010-12-01 2012-09-07 Woodward Fst, Inc. Hybrid variable area fuel injector with thermal protection
EP2520858A1 (en) 2011-05-03 2012-11-07 Siemens Aktiengesellschaft Fuel cooled pilot fuel lance for a gas turbine
US20140223913A1 (en) * 2013-02-08 2014-08-14 Robert James Fanella Forged fuel injector stem
EP3460334A1 (en) * 2017-09-25 2019-03-27 Delavan, Inc. Electronic fuel control for gas turbine engines
US20220196241A1 (en) * 2020-12-18 2022-06-23 Pratt & Whitney Canada Corp. Gap filler for a fuel system gallery
EP4328436A1 (en) * 2022-08-26 2024-02-28 Hamilton Sundstrand Corporation Proportional restriction of fuel nozzle with an auxiliary circuit
US11970976B2 (en) 2022-08-26 2024-04-30 Hamilton Sundstrand Corporation Variable restriction of fuel nozzle with an auxiliary circuit
US12313004B2 (en) 2022-08-26 2025-05-27 Collins Engine Nozzles, Inc. Proportional force modification of passive spool for control of secondary nozzle circuits

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US2959360A (en) * 1957-09-20 1960-11-08 Alco Products Inc Fuel injectors
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US3131866A (en) * 1961-12-07 1964-05-05 Clessie L Cummins Fuel injector
US3154095A (en) * 1962-09-28 1964-10-27 Parker Hannifin Corp Flow divider for dual-orifice fuel injection nozzle
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US2592111A (en) * 1948-12-30 1952-04-08 Bischof Bernhard Injector for internal-combustion engines
US2959360A (en) * 1957-09-20 1960-11-08 Alco Products Inc Fuel injectors
US3029029A (en) * 1959-05-26 1962-04-10 Parker Hannifin Corp Dual-orifice return flow nozzle
US3131866A (en) * 1961-12-07 1964-05-05 Clessie L Cummins Fuel injector
US3154095A (en) * 1962-09-28 1964-10-27 Parker Hannifin Corp Flow divider for dual-orifice fuel injection nozzle
US3379374A (en) * 1966-08-22 1968-04-23 Gen Motors Corp Fuel injection device
US3387790A (en) * 1967-04-11 1968-06-11 Bosch Arma Corp Fuel injection nozzle

Cited By (66)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4111365A (en) * 1973-12-26 1978-09-05 Isuzu Motors Limited Fuel injection system and its nozzle holder
US4111369A (en) * 1977-07-05 1978-09-05 General Motors Corporation Fuel nozzle
FR2471480A1 (en) * 1979-12-13 1981-06-19 Snecma INJECTION DEVICE FOR A COMBUSTION CHAMBER FOR A TURBINE ENGINE
EP0030880B1 (en) * 1979-12-13 1983-08-31 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Injection device for the combustion chamber of a turbine engine
US4409791A (en) * 1979-12-13 1983-10-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.L.M.A." Injection device for the combustion chamber of turbine engines
FR2540186A1 (en) * 1983-01-27 1984-08-03 Ex Cell O Corp PRESSURE ATOMIZED FUEL INJECTOR
US4491272A (en) * 1983-01-27 1985-01-01 Ex-Cell-O Corporation Pressure atomizing fuel injection assembly
EP0132213A3 (en) * 1983-07-19 1986-02-12 United Technologies Corporation Fuel nozzle for gas turbine engine
FR2622634A1 (en) * 1987-11-04 1989-05-05 United Technologies Corp FUEL INJECTOR ASSEMBLY FOR AN AXIAL FLOW ROTATING MACHINE AND METHOD OF PROTECTING FUEL ARISING IN A PASSAGE THEREWITH
GB2211926A (en) * 1987-11-04 1989-07-12 United Technologies Corp Fuel nozzle assembly
US4898329A (en) * 1987-11-04 1990-02-06 United Technologies Corporation Apparatus for a fuel system
GB2211926B (en) * 1987-11-04 1991-07-03 United Technologies Corp Apparatus for a fuel system
FR2626043A1 (en) * 1988-01-14 1989-07-21 Gen Electric TURBULENCE-FUEL INJECTOR FORMATION DEVICE FOR A COMBUSTION ASSEMBLY IN A GAS TURBINE
US4938418A (en) * 1988-12-01 1990-07-03 Fuel Systems Textron Inc. Modular fuel nozzle assembly for gas turbine engines
US5269468A (en) * 1992-06-22 1993-12-14 General Electric Company Fuel nozzle
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US6141968A (en) * 1997-10-29 2000-11-07 Pratt & Whitney Canada Corp. Fuel nozzle for gas turbine engine with slotted fuel conduits and cover
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