EP1793165A2 - Injecteur de carburant liquide, chambre de combustion de turbine à gaz, et méthode pour reconfigurer une chambre de combustion de turbine à gaz - Google Patents

Injecteur de carburant liquide, chambre de combustion de turbine à gaz, et méthode pour reconfigurer une chambre de combustion de turbine à gaz Download PDF

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Publication number
EP1793165A2
EP1793165A2 EP06024947A EP06024947A EP1793165A2 EP 1793165 A2 EP1793165 A2 EP 1793165A2 EP 06024947 A EP06024947 A EP 06024947A EP 06024947 A EP06024947 A EP 06024947A EP 1793165 A2 EP1793165 A2 EP 1793165A2
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EP
European Patent Office
Prior art keywords
fuel
nozzle
main
pilot
injection hole
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Withdrawn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
EP06024947A
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German (de)
English (en)
Other versions
EP1793165A3 (fr
Inventor
Yoshitaka Hirata
Shouhei Yoshida
Toshifumi Sasao
Isao Takehara
Hiroshi Inoue
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.)
Hitachi Ltd
Original Assignee
Hitachi 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 Hitachi Ltd filed Critical Hitachi Ltd
Priority to EP11162240A priority Critical patent/EP2385299A3/fr
Publication of EP1793165A2 publication Critical patent/EP1793165A2/fr
Publication of EP1793165A3 publication Critical patent/EP1793165A3/fr
Withdrawn legal-status Critical Current

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    • 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
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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

Definitions

  • the present invention relates to a liquid fuel nozzle, a gas turbine combustor, a liquid fuel nozzle of a gas turbine combustor, and a method of rebuilding a gas turbine combustor.
  • liquid fuel is jetted out of a liquid fuel nozzle in the atomized form and is combusted while promoting mixing of small-diameter fuel particles with air for combustion.
  • a liquid fuel nozzle of the so-called one-fluid type is known as a nozzle which does not require the high pressure air or the like.
  • the supply pressure of liquid fuel is raised to increase the injection speed of the liquid fuel, thereby atomizing the liquid fuel.
  • the initial cost can be reduced because of no necessity of using the compressor for supplying atomization air and the associated auxiliaries.
  • Another advantage is that the bleed air introduced from the compressor to serve as a supply source of the atomization air is also no longer required, and the efficiency of the gas turbine is not reduced.
  • the one-fluid type liquid fuel nozzle accompanies with a possibility that atomization of the liquid fuel is degraded in the range of low fuel flow rate where the injection speed of the liquid fuel is small. Also, there is a possibility that, in the range of low fuel flow rate such as in the ignition stage of a combustor, the atomization is not promoted, whereby ignition is failed and an exhaust amount of colored smoke is increased with the failed ignition.
  • Patent Document 1 JP,B 7-62522 discloses a dual orifice fuel nozzle having a primary fuel nozzle for jetting liquid fuel while applying a swirl component to the liquid fuel about the axis of the fuel nozzle, and a secondary fuel nozzle positioned around the primary fuel nozzle and jetting the liquid fuel while applying a swirl component to the liquid fuel similarly to the primary fuel nozzle.
  • the liquid fuel can be jetted out of the secondary fuel nozzle in addition to the primary fuel nozzle.
  • the liquid fuel can be atomized with superior atomization performance over a wide range from the startup to the high-load condition without causing an excessive rise of the fuel supply pressure.
  • a combustor installed in a gas turbine plant ranging from the medium to large size is constituted by a plurality of units, and a liquid fuel nozzle is also mounted in plural correspondingly.
  • flow rate characteristics of the liquid fuel nozzles i.e., the relationships between respective flow rates of the atomized fuel from the nozzles and the fuel supply pressure, are desired to be even. The reason is as follows. If the flow rate characteristics of the liquid fuel nozzles are not even, a deviation occurs among the temperatures of combustion gases produced from the combustors, and the combustion gases having the temperature deviation are supplied to a turbine downstream of the combustors. Therefore, the efficiency of power generation may be reduced and the life span of a turbine blade may be shortened.
  • an object of the present invention is to hold even the flow rate of fuel jetted out of each liquid fuel nozzle without degrading atomization performance of the fuel nozzle mounted in each combustor.
  • a liquid fuel nozzle of the present invention is featured in that a main injection hole for jetting main fuel is of a structure having a straight portion which is in the form of an annular flow path extending parallel to an axis of the liquid fuel nozzle, the annular flow path having a flow path cross section not changed along the straight portion.
  • a deviation of the fuel flow rate can be suppressed without degrading the atomization performance of each liquid fuel nozzle mounted in each combustor, and a liquid fuel nozzle with high reliability can be obtained.
  • Fig. 6 shows the structure of a fuel nozzle of Comparative Example 1.
  • the fuel nozzle comprises a nozzle cover 201, a secondary chip 204, a primary chip 203, and a nozzle block 202.
  • the primary chip 203 includes a primary swirler 205 for applying a swirl component to liquid fuel, a primary swirl chamber 211, and a primary injection hole 209.
  • Primary liquid fuel supplied through the primary fuel path 207 is given with a swirl component by the primary swirler 205 such that the primary liquid fuel is swirled in the primary swirl chamber 211 and is jetted out of the primary injection hole 209 in the form of a bell-shaped (substantially conical) spray.
  • a primary fuel nozzle is constituted by the primary fuel path 207, the primary swirler 205, the primary swirl chamber 211, and the primary injection hole 209.
  • secondary liquid fuel is given with a swirl component by the secondary swirler 206 such that the secondary liquid fuel is swirled in the secondary swirl chamber 212 and is jetted out of the secondary injection hole 210.
  • a secondary fuel nozzle is constituted by the secondary fuel path 208, the secondary swirler 206, the secondary swirl chamber 212, and the secondary injection hole 210.
  • the flow path cross section of the secondary injection hole 210 is given by the cross section of an annular flow path constituted by a gap between a throttle portion 213 inside the secondary chip 204 and an outer peripheral wall surface of the primary chip 203.
  • the outer peripheral wall surface of the primary chip 203 deciding the flow path cross section of the secondary injection hole 210 has a tapered conical geometry, and it is very difficult to control the dimensions of outer and inner peripheral surfaces of the conical primary chip 203.
  • the flow path cross section of the secondary injection hole 210 is changed if the relative positional relationship between the primary chip 203 and the secondary chip 204 in the axial direction is changed.
  • the fuel nozzle such as shown as Comparative Example 1 is assembled by inserting the nozzle block 202, the primary chip 203, and the secondary chip 204 in the nozzle cover 201, and fixedly holding them together by using threads formed on the nozzle cover 201 and a nozzle body 214 for screw-in mount.
  • tightening torque is controlled when the nozzle cover 201 is fastened to the nozzle body 214, the relative positional relationship between the primary chip 203 and the secondary chip 204 in the axial direction is changed if the tightening torque is changed. Therefore, a deviation occurs in the flow rate characteristic of the fuel nozzle and the fuel flow rate becomes uneven.
  • Figs. 7A, 7B and 7C show, as Comparative Example 2, one example of means for applying a swirl component to fuel.
  • Fig. 7A is a longitudinal sectional view of a fuel nozzle of Comparative Example 2
  • Fig. 7B is a sectional view taken along line B-B in the direction of arrows in Fig. 7A
  • Fig. 7C is a sectional view taken along line C-C in Fig. 7B.
  • the fuel nozzle of Comparative Example 2 comprises a nozzle cover 300, a nozzle chip 301, and a nozzle body 302. As shown in Fig.
  • the swirling direction of fuel 307 is given by forming a plurality of fuel holes 306 in the nozzle chip 301 to obliquely extend in the direction toward a fuel injection hole 305 at an elevation angle ⁇ with respect to a section of the fuel nozzle taken along the line B-B.
  • a swirl component is given to the fuel 307 having passed through the fuel holes 306.
  • swirling flows are formed in a swirl chamber 308 defined by the nozzle cover 300 and the nozzle chip 301 and are jetted out of the injection hole 305.
  • the fuel having passed through the fuel holes 306 forms flows while being subjected to actions of not only swirling components in the circumferential direction, but also axial components.
  • the fuel holes 306 are formed obliquely with respect to the surface of the nozzle chip 301 from which is jetted the fuel. It is therefore difficult to machine the fuel holes 306.
  • the fuel having passed through the fuel holes 306 is subjected to actions of not only the swirling components in the circumferential direction, but also the axial components, there is a possibility that the swirling components in the circumferential direction are reduced correspondingly.
  • the fuel cannot be sufficiently given with the swirling components in the circumferential direction, and fuel atomization performance is reduced.
  • Fig. 3 is a diagram schematically showing the overall construction of a gas turbine plant.
  • the gas turbine plant mainly comprises a compressor 1 for compressing air and producing high pressure air 13 for combustion, a combustor 3 for mixing the high pressure air 13 introduced for combustion from the compressor 1 and fuel with each other and producing combustion gas 14, and a turbine 2 to which is introduced the combustion gas 14 produced by the combustor 3.
  • a shaft of the compressor 1 and a shaft of the turbine 2 are coupled to each other.
  • the combustor 3 is a pressure vessel which includes an inner casing 7 for producing the combustion gas 14 therein, a liquid fuel nozzle 9 for atomizing liquid fuel, a swirler 10 for applying a swirl component to the high pressure air 13 for combustion, and an ignition plug 11 for igniting the fuel, and which is enclosed by an outer casing 5 and an end cover 6.
  • the liquid fuel nozzle 9 for injecting the liquid fuel is disposed at a position on the axis of the inner casing 7 in the upstream side.
  • the swirler 10 for holding a diffusion flame 16 is disposed around the liquid fuel nozzle 9, and an inner casing cap 12 is disposed around the swirler 10.
  • Fig. 3 looking at the combustion gas 14 flowing through the interior of the inner casing 7, the side in which is disposed the liquid fuel nozzle 9 represents the upstream side, and the direction in which is supplied the combustion gas 14 toward the turbine 2 represents the downstream direction (downstream side).
  • the high pressure air 13 introduced for combustion from the compressor 1 passes through an annular air path defined by the outer casing 5 and the inner casing 7 and is introduced to the interior of the inner casing 7 through combustion holes and cooling holes, which are formed in a wall of the inner casing 7 and the inner casing cap 12, and through the swirler 10.
  • the air supplied to the inner casing 7 is mixed with the fuel, and a resulting gas mixture is ignited by the ignition plug 11 and combusted inside the inner casing 7.
  • the combustion gas 14 produced with the combustion of the gas mixture is supplied to the turbine 2 through a transition piece 8, thereby driving the turbine 2.
  • a generator 4 coupled to the turbine 2 is driven to generate electric power.
  • Fig. 2 shows details of the fuel supply system for the liquid fuel nozzle 9.
  • the liquid fuel nozzle 9 according to this first embodiment is divided into a pilot system which ensures superior atomization performance under the condition of low fuel flow rate such as in the ignition stage, and a main system which enables the fuel to be jetted under the condition of large fuel flow rate, such as the condition of high load, without excessively raising the supply pressure.
  • a pressurization valve 29 is disposed in the downstream side of a main flow path 35, and the main flow path 35 is joined with a pilot flow path 34 at a distribution pipe 36 disposed upstream of the main flow path 35.
  • a check valve 28 is disposed upstream of the distribution pipe 36 and is connected to the fuel supply system including the above-described pumps, valves, etc.
  • a purge air flow path 30 in the pilot system is communicated with still another end of the distribution pipe 36, and a main purge-air flow path 31 is communicated with the main flow path 35 at a position downstream of the pressurization valve 29.
  • a pilot purge air shutoff valve 37 Upstream of the purge air flow path 30 and the main purge-air flow path 31, there are disposed a pilot purge air shutoff valve 37, a main purge-air shutoff valve 38, a pressure control valve 39, and a purge air compressor 27.
  • the fuel supplied from the high pressure pump 21 is distributed to the respective combustors by the flow divider 26 and is introduced to the distribution pipe 36 through the check valve 28.
  • the check valve 28 serves to prevent the air for combustion, the combustion gas, the purge air, etc. from flowing backward toward the auxiliaries in the fuel supply system, such as the pumps.
  • the fuel supplied to the distribution pipe 36 is distributed to the pilot flow path 34 and the main flow path 35.
  • the fuel pressure acting on the pressurization valve 29 disposed midway the main flow path 35 is so low as to be not able to open the pressurization valve 29, and the fuel is supplied to only the pilot flow path 34.
  • the operation of stopping the gas turbine will be described in brief below.
  • the fuel remaining inside the liquid fuel nozzle 9 may cause coking, i.e., a phenomenon that the fuel is carbonized by receiving heat from various components of the combustor and is fixedly stuck to the interior of the liquid fuel nozzle 9.
  • the fuel injection hole is closed and the fuel cannot be jetted out of the fuel injection hole.
  • the liquid fueled combustor includes means for supplying, e.g., air, for the purpose of discharging the fuel residing in the liquid fuel nozzle to a combustion chamber.
  • the pilot flow path 34 and the main flow path 35 also include means for supplying purge air for the same purpose. More specifically, after the gas turbine has been stopped, purge air supplied from the purge air compressor 27 is controlled to have a predetermined pressure by the pressure control valve 39 and then supplied to the pilot and main flow paths of the liquid fuel nozzle through the pilot and main purge-air shutoff valves 37 and 38.
  • the purge air is supplied to only the main flow path 35 such that the atomization of the fuel jetted out of a pilot nozzle can be assisted by the purge air jetted out of a main nozzle. Accordingly, it is possible to promote the atomization of the fuel jetted out of the pilot nozzle, and to increase reliability of ignition.
  • Figs. 1A and 1B show the detailed structure of a front end portion of the dual orifice liquid fuel nozzle according to this first embodiment, i.e., the liquid fuel nozzle 9 provided with the above-described fuel supply system.
  • Fig. 1A is a longitudinal sectional view of the liquid fuel nozzle 9
  • Fig. 1B is a sectional view taken along line A-A in the direction of arrows in Fig. 1A.
  • the liquid fuel nozzle 9 comprises a nozzle cap 100, a nozzle chip 101, a pilot chip 102, and a nozzle body 103.
  • the pilot chip 102 is contained inside the nozzle chip 101.
  • the nozzle chip 101 is contained inside the nozzle cap 100.
  • the pilot chip 102 and the nozzle chip 102 are fixedly held together by using threads formed on the nozzle body 103 and the nozzle cap 100 for screw-in mount. Further, a main swirler 106 is disposed on the outer peripheral side of the nozzle chip 101. Incidentally, the nozzle cap 100 and the nozzle chip 101 are firmly held in place by strongly pressing the nozzle body 103 against the nozzle chip 101 at a contact surface between them.
  • the nozzle body 103 has a pilot flow path 105 and a main flow path 104 which are connected respectively to pilot and main supply systems for the pilot chip 102 and the nozzle chip 101.
  • the pilot chip 102 has a pilot swirl chamber 110 which is defined by the pilot chip 102 and the nozzle chip 101, and a pilot swirl hole 107 is formed to extend in the tangential direction of the pilot swirl chamber 110.
  • Pilot fuel 32 supplied through the pilot flow path 105 flows into the pilot swirl hole 107 from the outer circumference of the pilot chip 102 and is given with a swirl component such that the pilot fuel 32 is swirled inside the pilot swirl chamber 110. Further, the pilot fuel 32 forms a liquid thin film along the wall surface of the pilot swirl chamber 110, and is jetted out of a pilot injection hole 108 in the form of droplets.
  • Main fuel 33 supplied through the main flow path 104 passes through a main fuel supply hole 112 formed in the nozzle chip 101 and flows into the main swirler 106 through an annular flow path 113 which is defined by the nozzle cap 100 and the nozzle chip 101.
  • the main fuel 33 is given with a swirl component by the main swirler 106 such that the main fuel 33 is swirled inside a main swirl chamber 111 which is defined by the inner peripheral wall of the nozzle cap 100 and the outer peripheral wall of the nozzle chip 101, followed by being jetted out of a main injection hole 109.
  • the pilot injection hole 108 is disposed inside the nozzle cap 100 and has the function of jetting the pilot fuel from it. Also, the pilot injection hole 108 is defined by a space between the pilot swirl chamber 110 formed in the nozzle chip 101 and a distal end portion of the nozzle chip 101 from which is jetted the pilot fuel 32 toward the combustion chamber.
  • the main injection hole 109 is disposed inside the nozzle cap 100 and has the function of jetting the main fuel from it. Also, the main injection hole 109 is defined by a space between the swirl chamber 111 for swirling the main fuel, which has been given with the swirl component by the main swirler 106, and the distal end portion of the nozzle chip 101 from which is jetted out of the pilot fuel 32 toward the combustion chamber.
  • the main injection hole 109 is in the form of an annular flow path defined between the outer peripheral surface of the nozzle chip 101 and the inner peripheral surface of the nozzle cap 100.
  • the swirl chamber 111 communicates the main swirler 106 and the main injection hole 109 with each other such that the main fuel having been jetted out of the annular flow path 113 is supplied to the main injection hole 109 while being swirled.
  • the swirl chamber 111 is constituted as an annular flow path defined between the conically-recessed inner peripheral surface of the nozzle cap 100 and the conical outer peripheral surface of the nozzle chip 101.
  • the roles of the main supply system and the pilot supply system will be described below.
  • the pilot supply system serves to promote the atomization of the fuel by raising the fuel supply pressure even under the condition of low fuel flow rate such as in the ignition stage.
  • the main supply system serves to enable the fuel to be jetted without excessively raising the fuel supply pressure even under the condition of high load where a large fuel flow rate is required. Under the condition of high load, therefore, a most part of the fuel flow rate is supplied through the main supply system.
  • the main injection hole 109 defined by the nozzle cap 100 and the nozzle chip 101 is of a structure having a straight portion which is in the form of an annular flow path extending parallel to the axis of the liquid fuel nozzle and which has a flow path cross section not changed along the straight portion.
  • the flow rates of fuel supplied to the individual combustors are desired to be even.
  • the flow divider 26 for distributing the fuel to the individual combustors has a structure capable of evenly distributing the fuel.
  • an allowable limit of the fuel divider 26 for ensuring even distribution is exceeded and the fuel cannot be evenly distributed in some cases.
  • a most part of the fuel flow rate is occupied by the main fuel 33 jetted through the main supply system.
  • the flow rate of the fuel jetted through the main supply system is dominated by the main injection hole 109 which has a minimum flow path cross section in the main supply system.
  • the cross section of the main injection hole 109 is the cross section of the main supply system at the most downstream side of the pilot flow path formed by the nozzle chip 101 (i.e., at the end of the pilot injection hole 108). It is therefore important to reduce a variation in the flow path cross section of the main injection hole 109 from the viewpoint of reducing the flow deviation.
  • the secondary injection hole 210 corresponding to the main injection hole 109 in the first embodiment is provided as the annular flow path constituted by the gap between the throttle portion 213 inside the secondary chip 204 and the outer peripheral wall surface of the primary chip 203.
  • the outer peripheral wall surface of the primary chip 203 deciding the flow path cross section of the secondary injection hole 210 has a tapered conical geometry, and it is very difficult to control the dimensions of outer and inner peripheral surfaces of the conical primary chip 203.
  • the fuel nozzle such as shown as Comparative Example 1 is assembled by inserting the nozzle block 202, the primary chip 203, and the secondary chip 204 in the nozzle cover 201, and fixedly holding them together by using threads formed on the nozzle cover 201 and the nozzle body 214 for screw-in mount.
  • the nozzle cover 201 is fastened to the nozzle body 214, tightening torque is controlled.
  • the tightening torque is changed, the relative positional relationship between the primary chip 203 and the secondary chip 204 in the axial direction is changed. Therefore, the flow path cross section of the secondary injection hole 210 is further changed, thus causing the flow deviation with respect to the other fuel nozzles.
  • the main injection hole 109 is provided as an annular flow path having a straight portion which is defined by an inner peripheral wall 114 at the distal end of the nozzle cap 100 and an outer peripheral wall 115 at the distal end of the nozzle chip 101. That structure facilitates machining of the nozzle cap 100 and the nozzle chip 101 which decide the cross section of the main injection hole 109. Further, since machining accuracy is improved, another advantage is also obtained in that a variation in the cross section of the main injection hole caused by manufacturing errors can be reduced.
  • the advantages of the liquid fuel nozzle according to this first embodiment can also be obtained by rebuilding the existing fuel nozzle.
  • the existing fuel nozzle such as shown as Comparative Example 1 can be rebuilt as follows. After removing the nozzle cover 201, the inner components, i.e., the secondary chip 204, the primary chip 203, and the nozzle block 202, are also disassembled. Then, the pilot chip 102 and the nozzle chip 101 according to this first embodiment are mounted to the nozzle body 214. Finally, the nozzle cap 100 is fitted in place.
  • the advantages of this first embodiment can be obtained just by replacing some parts with no need of renewing the entire fuel nozzle.
  • FIG. 4 is a longitudinal sectional view of the liquid fuel nozzle according to this second embodiment.
  • Basic components constituting the liquid fuel nozzle are the same as those in the first embodiment.
  • the pilot injection hole 108 and the main injection hole 109 are formed such that their distal ends are located at the same position in the axial direction.
  • the distal end of the pilot injection hole 108 is positioned upstream of the distal end of the main injection hole 109. This is because the first embodiment is intended to assist the atomization of the fuel jetted out of the pilot nozzle by the purge air jetted out of the main nozzle.
  • the distal end of the pilot injection hole 108 By arranging the distal end of the pilot injection hole 108 to be positioned upstream of the distal end of the main injection hole 109, mixing of the purge air jetted out of the main nozzle and the fuel jetted out of the pilot nozzle can be promoted and an atomization characteristic under the condition in the ignition stage can be improved.
  • fuel droplets 116 jetted out of the pilot injection hole 108 may collide against fuel droplets 117 jetted out of the main injection hole 109 under the condition of high load where the fuel is supplied through both the pilot and main injection holes and the fuel flow rate is large.
  • FIG. 5A is a longitudinal sectional view of the liquid fuel nozzle according to this third embodiment
  • Fig. 5B is a sectional view taken along line D-D in the direction of arrows in Fig. 5A.
  • Basic components in this third embodiment are the same as those in the first embodiment.
  • the main fuel supply holes 112 are formed such that each hole is positioned at a shift of phase by an angle ⁇ in the circumferential direction with respect to an inlet of the main swirler 106 as a basis.
  • the main fuel 33 having passed through the main fuel supply holes 112 flows into the annular flow path 113 and temporarily resides in the annular flow path 113. Thereafter, the main fuel 33 is evenly distributed to the plurality of swirl flow paths 150 constituting the main swirler 106.
  • the main fuel 33 having been jetted out of the main fuel supply holes 112 can be avoided from directly flowing into the swirl flow paths 150 even under the condition of small flow rate.
  • the main fuel since the main fuel temporarily resides in the annular flow path 113, it is possible to reduce the deviation in the flow rate of the fuel supplied to the swirl flow path 150, and to jet the fuel without degrading the atomization characteristic.
  • the present invention can be widely applied to a variety of liquid fuel nozzles used for combusting liquid fuel in addition to that used in the gas turbine combustor.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP06024947A 2005-12-02 2006-12-01 Injecteur de carburant liquide, chambre de combustion de turbine à gaz, et méthode pour reconfigurer une chambre de combustion de turbine à gaz Withdrawn EP1793165A3 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11162240A EP2385299A3 (fr) 2005-12-02 2006-12-01 Buse de fuel liquide pour chambre de combustion à gaz et procédé de reconstruction d'une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2005348619A JP2007155170A (ja) 2005-12-02 2005-12-02 燃料ノズル，ガスタービン燃焼器，ガスタービン燃焼器の燃料ノズル及びガスタービン燃焼器の改造方法

Publications (2)

Publication Number Publication Date
EP1793165A2 true EP1793165A2 (fr) 2007-06-06
EP1793165A3 EP1793165A3 (fr) 2009-02-25

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EP06024947A Withdrawn EP1793165A3 (fr) 2005-12-02 2006-12-01 Injecteur de carburant liquide, chambre de combustion de turbine à gaz, et méthode pour reconfigurer une chambre de combustion de turbine à gaz
EP11162240A Withdrawn EP2385299A3 (fr) 2005-12-02 2006-12-01 Buse de fuel liquide pour chambre de combustion à gaz et procédé de reconstruction d'une turbine à gaz

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EP11162240A Withdrawn EP2385299A3 (fr) 2005-12-02 2006-12-01 Buse de fuel liquide pour chambre de combustion à gaz et procédé de reconstruction d'une turbine à gaz

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Cited By (15)

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CN101876438A (zh) * 2009-04-30 2010-11-03 通用电气公司 用于涡轮发动机的大体积燃料喷嘴
CH702598A1 (de) * 2010-01-29 2011-07-29 Alstom Technology Ltd Einspritzdüse sowie Verfahren zum Betrieb einer solchen Einspritzdüse.
US8082724B2 (en) 2007-11-29 2011-12-27 Hitachi, Ltd. Combusting system, remodeling method for combusting system, and fuel injection method for combusting system
CN103292351A (zh) * 2012-02-28 2013-09-11 株式会社日立制作所 燃气轮机燃烧器
WO2015174880A1 (fr) * 2014-05-12 2015-11-19 General Electric Company Cartouche de combustible liquide avant la formation de film
EP2832451A4 (fr) * 2012-03-28 2015-12-23 Fujisaki Electric Co Ltd Appareil d'éjection de liquide et procédé d'éjection de liquide
EP2629016A3 (fr) * 2012-02-16 2017-05-17 Delavan Inc. Injection multipoint à angle variable
RU189000U1 (ru) * 2018-10-09 2019-05-06 Федеральное государственное бюджетное образовательное Учреждение высшего образования "Воронежский государственный аграрный университет имени императора Петра 1" (ФГБОУ ВО Воронежский ГАУ) Центробежная форсунка
RU188999U1 (ru) * 2018-10-09 2019-05-06 Федеральное государственное бюджетное образовательное Учреждение высшего образования "Воронежский государственный аграрный университет имени императора Петра 1" (ФГБОУ ВО Воронежский ГАУ) Многотопливная форсунка
WO2019241108A1 (fr) * 2018-06-11 2019-12-19 Woodward, Inc. Pointe d'atomisation à pression de pré-tourbillonnement
RU2744963C1 (ru) * 2020-06-09 2021-03-17 Акционерное общество "Металлист-Самара" Камера сгорания газотурбинной установки с выносными жаровыми трубами и малоэмиссионным горелочным устройством
CN112780416A (zh) * 2021-01-29 2021-05-11 安徽应流航空科技有限公司 一种主燃油分配结构
RU2763964C1 (ru) * 2019-12-30 2022-01-11 Публичное акционерное общество "ОДК-Кузнецов" (ПАО "ОДК-Кузнецов") Двухконтурная горелка малоэмиссионной камеры сгорания газотурбинного двигателя
US20220333554A1 (en) * 2018-11-15 2022-10-20 Stratolaunch, Llc Swirl preburner system and method
EP4050261A4 (fr) * 2019-10-23 2023-11-22 IHI Corporation Injecteur de combustible liquide

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CN102057145B (zh) 2008-06-09 2014-08-20 西门子公司 用于冲洗燃气轮机的燃料系统的方法以及从属的燃料系统
FR2938048B1 (fr) * 2008-11-06 2015-03-06 Ge Energy Products France Snc Systeme et procede de lavage et purge a l'eau du circuit combustible liquide d'une turbine
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