EP3049722A1 - Lance injector for injecting fuel oil into a gas turbine combustion chamber - Google Patents

Lance injector for injecting fuel oil into a gas turbine combustion chamber

Info

Publication number
EP3049722A1
EP3049722A1 EP14796263.3A EP14796263A EP3049722A1 EP 3049722 A1 EP3049722 A1 EP 3049722A1 EP 14796263 A EP14796263 A EP 14796263A EP 3049722 A1 EP3049722 A1 EP 3049722A1
Authority
EP
European Patent Office
Prior art keywords
tubular body
injector
outer tubular
inner tubular
nozzle
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.)
Granted
Application number
EP14796263.3A
Other languages
German (de)
French (fr)
Other versions
EP3049722B1 (en
Inventor
Pierpaolo Pastorino
Rocco Galella
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.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP3049722A1 publication Critical patent/EP3049722A1/en
Application granted granted Critical
Publication of EP3049722B1 publication Critical patent/EP3049722B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—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
    • F23D11/28—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 with flow-back of fuel at the burner, e.g. using by-pass

Definitions

  • the present invention relates to a lance injector for injecting fuel oil into a gas turbine combustion chamber.
  • gas turbines especially if used in plants for the production of electric energy, may be supplied with various types of fuel.
  • gas turbines especially if used in plants for the production of electric energy, may be supplied with various types of fuel.
  • gas turbines may run gas turbines on gaseous fuels of various nature and features (natural gas, syngas) or on fuel oils, such as diesel.
  • the gas turbines are provided with burner assemblies which comprise injectors, normally of the lance type, specifically designed to supply a controlled flow rate of fuel oil.
  • the lance injectors generally comprise a plurality of coaxial tubular bodies, on the end of which a terminal provided with a nozzle is mounted.
  • the tubular bodies define, between one another, at least one delivery line between an inlet and the nozzle and a return line, which allows to recover the fuel in excess supplied to the nozzle. Possibly, a water supply line may be present.
  • a problem often present in lance injectors is due to the different thermal expansion of the components in use, with particular reference to the tubular bodies.
  • the thermal stresses are considerable as a result of the very high temperatures in the combustion chamber (i.e. near the terminal and the nozzle) .
  • the consequent thermal expansions are not only remarkable, but also differ greatly from one component to the other, by effect of the differences of geometry and of exposure to the high temperatures of the combustion chamber and to the cooling air conveyed from the outside or to the process fluid.
  • a lance injector for injecting fuel oil into a gas turbine combustion chamber is provided as defined in claim 1.
  • FIG. 1 is a side section view, taken along an axial longitudinal plane and with parts removed for clarity, of a burner of a gas turbine incorporating a lance injector according to an embodiment of the present invention
  • figure 2 is a first enlarged detail of the lance injector in figure 1 ;
  • figure 3 is a variant of the detail in figure 2, according to a different embodiment of the present invention.
  • figure 4 is a second enlarged detail of the lance injector in figure 1.
  • reference numeral 1 indicates as a whole a burner assembly for supplying fuel, in particular a gas, into a gas turbine combustion chamber 2, shown only partially here.
  • the burner assembly 1 extends along an axis A and comprises a peripheral gas main burner 3, a central gas pilot burner 4, and a lance injector 5 for injecting fuel oil into the combustion chamber 2.
  • the main burner 3 is of the pre-mixer type, is arranged about the pilot burner 4 and is provided with a diagonal swirler 7, which comprises a plurality of vanes 10, mutually defining respective flow channels to convey a flow of combustion supporting air and fuel gas towards the combustion chamber 2 obliquely with respect to axis A.
  • the fuel gas is supplied through nozzles 11 placed on the vanes 10.
  • the pilot burner 4 is arranged coaxial to the main burner 3 and is provided with an axial swirler 8, which comprises a plurality of vanes 12, mutually defining respective flow channels to convey a further flow of combustion supporting air towards the combustion chamber 2, substantially along axis A.
  • the lance injector 5 extends along axis A and has an end inserted within the pilot burner 4.
  • the lance injector 5 comprises an outer tubular body 15, an inner tubular body 16, an end member 17 and a nozzle 18. Furthermore, the lance injector 5 is provided with flanges 20, 21.
  • the fluid delivery line 22 is defined by a gap between the outer tubular body 15 and the inner tubular body 16 and allows to convey a fuel oil flow to the nozzle 18.
  • the fluid return line 23 is instead defined in the inner tubular body 16 and allows to recover the fuel oil supplied in excess to the nozzle 18 and to re-introduce it into a manifold (not shown) .
  • An axial pin 24 is housed in the inner tubular body 16, facing the nozzle 18, and is configured so as to adjust the return flow of the fuel oil.
  • the nozzle 18 is fluily coupled to the fluid delivery line 22 and to the fluid return line 23 at respective ends 15a, 16a of the outer tubular body 15 and the inner tubular body 16.
  • the nozzle 18 is mounted on the end 16a of the inner tubular body 16 by threaded coupling or hot-fitted and comprises a lateral wall 26 delimiting a chamber 25 and having a supply outlet 25a facing outwards (in use, towards the combustion chamber 2) and a recovery outlet, 25b, axially opposite to the supply outlet 25a and coupled to the fluid return line 23.
  • the end member 17 is fitted onto the end 15a of the outer tubular body 15 and coupled thereto by threaded coupling or possibly hot-fitted.
  • the nozzle 18 and the end member 17 are connected interferentially and the nozzle 18 projects axially outwards with respect to the end member 17.
  • the end member 17 defines internally a fluid passage 29 between the fluid delivery line 22 and the nozzle 18, the lateral wall 26 of which has inlet openings 25c for accessing the chamber 25.
  • the outer tubular body 15 and the inner tubular body 16 are constrained to each other at respective ends 15a, 16a so that the relative slide following thermal expansion is prevented in a locking region.
  • the relative slide between the outer tubular body 15 and of the inner tubular body 16 is free between the locking region and the opposite ends 15b, 16b, instead.
  • constraint members which, in one embodiment, comprise the end member 17 and a lock pin 27.
  • the lock pin 27 crosses the inner tubular body 16 and the axial pin 24 crosswise to axis A, for example perpendicularly.
  • the lock pin 27 is inserted with slight interference or welded in diametrically opposite seats of the inner tubular body 16 and is thus perpendicular to the axis A.
  • the lock pin 27 projects in opposite directions from the inner tubular body 16 and is arranged in front of an axial margin of the end 15a of the tubular body 15.
  • the length of the lock pin 27 is greater than the inner diameter and is substantially either equal to, or slightly greater than the outer diameter of the outer tubular body 15.
  • the end member 17 is configured so as to axially lock the lock pin 27 against the outer tubular body 15.
  • the end member 17 internally has an abutment seat 28, defined by an annular shoulder, of diameter smaller than the length of the lock pin 27.
  • the end member 17 is screwed onto the end 15a of the outer tubular body 15 so as to fit the ends of the lock pin 27 tightly between the axial margin of the end 15a of the outer tubular body 15 and the abutment seat 28.
  • the lock pin 27, tightly fitted by the end member 17, thus prevents the relative axial slide between the outer tubular body 15, the inner tubular body 16 and the axial pin 24 in the locking region.
  • the lock pin in a different embodiment, shown in figure 3, extends through the outer tubular body 15, the inner tubular body 16 and the axial pin 24, thus preventing the relative axial slide in the locking region.
  • the constraint members comprise a lock ring 30, which is tightly fitted onto the outer tubular body 15 and is coupled to the end member 17 so as to prevent respective relative rotations between the outer tubular body 15 and the end member 17, thus preventing the release of the threaded coupling.
  • the lock ring 30 is provided with axial teeth which engage respective seats of the end member 17.
  • the flange 20 extends along axis A and has a through axial cavity 31 and a radial fluid passage 32, communicating with the axial cavity 31, for supplying fuel oil to the fluid delivery line 22.
  • the axial cavity 31 ends with a neck 20a against which the end 15b of the outer tubular body 15 is arranged.
  • the neck 20a and the end 15b of the outer tubular body 15 may be welded to each other.
  • the end 16b of the inner tubular body 16 extends in the axial cavity 31 beyond the outer tubular body 15 and is inserted in a guide bushing 33, which belongs to the constraint members between the outer tubular body 15 and the inner tubular body 16.
  • the guide bushing 33 supports the inner tubular body 16 in centered position on axis A and allows the axial slide thereof, in particular following the thermal expansion of the portion closest to the combustion chamber 2. Furthermore, the guide bushing 33 ensures fluid-tightness against the lateral wall of the inner tubular body 15, thus preventing leakage of fuel oil.
  • the flange 21 is coupled to the flange 20 and has a through axial cavity 35, communicating with the end 16b of the inner tubular body 16 through the guide bushing 33 to recover the fuel oil in excess coming from the fluid return line 23.
  • the guide bushing 33 and the axial cavity 35 of the flange 21 define an expansion chamber which allow the free axial slide of the end 16b of the inner tubular body 16, which is free from axial constraints.
  • the described lance injector has many advantages. Firstly, one advantage derives from the fact that the relative axial slide constraint is closer to the hottest region of the injector in use, which is critical for the thermal and mechanical stresses and because the even partial obstruction of the fluid delivery and return lines must be avoided. The presence of the axial slide constraint causes the residual relative slide of the outer and inner tubular bodies and of the nozzle to be entirely negligible even following major differences of temperature. The opening of the fluid passages is thus ensured.
  • outer and inner tubular bodies which for their axial dimensions are subjected to higher expansions, are constrained to each other and to the end member without fitting, by inserting the lock pin and the threaded coupling between end member and outer tubular body. Consequently, there is no risk of damage or malfunctioning deriving from loss of interference between components.
  • the described lance injector is much less affected by the effects of the major thermal expansions caused by the high temperatures in the combustion chamber.
  • the considerable robustness of the lance injector according to the invention allows, in turn, to reduce significantly the cooling air flow rate for correct operation during operation with gas supplied by the main burner and/or the pilot burner. The general efficiency general of the gas turbine is thus increased.
  • the correct positioning of the components may be maintained both in use (i.e. in presence of high temperatures and major temperature differences between the opposite ends of the outer and inner tubular bodies) and in rest conditions, without needing to resort to contrast elements tending to promote the restoring of a given configuration (for example, packs of Belleville washers operating against the ends of one or both the tubular bodies) .
  • contrast elements tending to promote the restoring of a given configuration (for example, packs of Belleville washers operating against the ends of one or both the tubular bodies) .
  • the mechanical stresses and risks of failures are further reduced; on the other hand, the manufacturing of the lance injector is simplified.
  • Another advantage is given by the freedom of the outer and inner tubular bodies to expand in opposite direction with respect to the nozzle, where, by virtue of the chamber formed by the guide bushing and by the axial cavity, there are wide tolerances to allow relative axial slides without the risk of obstruction of passages and contact between various components. This aspect also contributes to reducing the risk of damage and malfunctions.

Landscapes

  • 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)
  • Fuel-Injection Apparatus (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Description

"LANCE INJECTOR FOR INJECTING FUEL OIL INTO A GAS TURBINE COMBUSTION CHAMBER"
TECHNICAL FIELD
The present invention relates to a lance injector for injecting fuel oil into a gas turbine combustion chamber.
BACKGROUND ART
As known, gas turbines, especially if used in plants for the production of electric energy, may be supplied with various types of fuel. In particular, it is known to run gas turbines on gaseous fuels of various nature and features (natural gas, syngas) or on fuel oils, such as diesel. For this reason, the gas turbines are provided with burner assemblies which comprise injectors, normally of the lance type, specifically designed to supply a controlled flow rate of fuel oil.
The lance injectors generally comprise a plurality of coaxial tubular bodies, on the end of which a terminal provided with a nozzle is mounted. The tubular bodies define, between one another, at least one delivery line between an inlet and the nozzle and a return line, which allows to recover the fuel in excess supplied to the nozzle. Possibly, a water supply line may be present.
A problem often present in lance injectors is due to the different thermal expansion of the components in use, with particular reference to the tubular bodies. The thermal stresses are considerable as a result of the very high temperatures in the combustion chamber (i.e. near the terminal and the nozzle) . The consequent thermal expansions are not only remarkable, but also differ greatly from one component to the other, by effect of the differences of geometry and of exposure to the high temperatures of the combustion chamber and to the cooling air conveyed from the outside or to the process fluid.
In turn, the different expansions produce intense mechanical stresses and may cause damage to the components, loss of fitting and malfunctioning in general. A fault which may often occur is the partial or total obstruction of the fuel oil fluid passages between the outlet of the delivery line, the nozzle and the inlet of the return line. In these cases, it is not possible to supply the required fuel oil supply correctly, with negative repercussions, for example on machine efficiency and on polluting emissions. In extreme cases, it may be necessary to stop the plant to replace the faulty injectors.
DISCLOSURE OF INVENTION
Thus, it is the object of the present invention to provide a lance injector for injecting fuel oil into a gas turbine combustion chamber which allows to overcome the described limitations.
According to the present invention, a lance injector for injecting fuel oil into a gas turbine combustion chamber is provided as defined in claim 1.
BRIEF DESCRIPTION OF THE DRAWINGS
The present invention will now be described with reference to the accompanying drawings, which illustrate some non-limitative embodiments thereof, in which:
- figure 1 is a side section view, taken along an axial longitudinal plane and with parts removed for clarity, of a burner of a gas turbine incorporating a lance injector according to an embodiment of the present invention;
- figure 2 is a first enlarged detail of the lance injector in figure 1 ;
- figure 3 is a variant of the detail in figure 2, according to a different embodiment of the present invention;
- figure 4 is a second enlarged detail of the lance injector in figure 1.
BEST MODE FOR CARRYING OUT THE INVENTION
In figure 1, reference numeral 1 indicates as a whole a burner assembly for supplying fuel, in particular a gas, into a gas turbine combustion chamber 2, shown only partially here. The burner assembly 1 extends along an axis A and comprises a peripheral gas main burner 3, a central gas pilot burner 4, and a lance injector 5 for injecting fuel oil into the combustion chamber 2.
The main burner 3 is of the pre-mixer type, is arranged about the pilot burner 4 and is provided with a diagonal swirler 7, which comprises a plurality of vanes 10, mutually defining respective flow channels to convey a flow of combustion supporting air and fuel gas towards the combustion chamber 2 obliquely with respect to axis A. In an embodiment, the fuel gas is supplied through nozzles 11 placed on the vanes 10.
The pilot burner 4 is arranged coaxial to the main burner 3 and is provided with an axial swirler 8, which comprises a plurality of vanes 12, mutually defining respective flow channels to convey a further flow of combustion supporting air towards the combustion chamber 2, substantially along axis A.
The lance injector 5 extends along axis A and has an end inserted within the pilot burner 4.
The lance injector 5 comprises an outer tubular body 15, an inner tubular body 16, an end member 17 and a nozzle 18. Furthermore, the lance injector 5 is provided with flanges 20, 21.
The outer tubular body 15 and the inner tubular body
16 extend concentrically along axis A and define fluid delivery line 22 and a fluid return line 23. More in detail, the fluid delivery line 22 is defined by a gap between the outer tubular body 15 and the inner tubular body 16 and allows to convey a fuel oil flow to the nozzle 18. The fluid return line 23 is instead defined in the inner tubular body 16 and allows to recover the fuel oil supplied in excess to the nozzle 18 and to re-introduce it into a manifold (not shown) . An axial pin 24 is housed in the inner tubular body 16, facing the nozzle 18, and is configured so as to adjust the return flow of the fuel oil.
With reference to figure 2, the nozzle 18 is fluily coupled to the fluid delivery line 22 and to the fluid return line 23 at respective ends 15a, 16a of the outer tubular body 15 and the inner tubular body 16. In particular, the nozzle 18 is mounted on the end 16a of the inner tubular body 16 by threaded coupling or hot-fitted and comprises a lateral wall 26 delimiting a chamber 25 and having a supply outlet 25a facing outwards (in use, towards the combustion chamber 2) and a recovery outlet, 25b, axially opposite to the supply outlet 25a and coupled to the fluid return line 23.
The end member 17 is fitted onto the end 15a of the outer tubular body 15 and coupled thereto by threaded coupling or possibly hot-fitted. The nozzle 18 and the end member 17 are connected interferentially and the nozzle 18 projects axially outwards with respect to the end member 17.
The end member 17 defines internally a fluid passage 29 between the fluid delivery line 22 and the nozzle 18, the lateral wall 26 of which has inlet openings 25c for accessing the chamber 25. The outer tubular body 15 and the inner tubular body 16 are constrained to each other at respective ends 15a, 16a so that the relative slide following thermal expansion is prevented in a locking region. The relative slide between the outer tubular body 15 and of the inner tubular body 16 is free between the locking region and the opposite ends 15b, 16b, instead.
The connection in the locking region is made by means of constraint members, which, in one embodiment, comprise the end member 17 and a lock pin 27.
The lock pin 27 crosses the inner tubular body 16 and the axial pin 24 crosswise to axis A, for example perpendicularly. In one embodiment, the lock pin 27 is inserted with slight interference or welded in diametrically opposite seats of the inner tubular body 16 and is thus perpendicular to the axis A. In one embodiment, the lock pin 27 projects in opposite directions from the inner tubular body 16 and is arranged in front of an axial margin of the end 15a of the tubular body 15. Furthermore, the length of the lock pin 27 is greater than the inner diameter and is substantially either equal to, or slightly greater than the outer diameter of the outer tubular body 15.
The end member 17 is configured so as to axially lock the lock pin 27 against the outer tubular body 15. In detail, the end member 17 internally has an abutment seat 28, defined by an annular shoulder, of diameter smaller than the length of the lock pin 27. The end member 17 is screwed onto the end 15a of the outer tubular body 15 so as to fit the ends of the lock pin 27 tightly between the axial margin of the end 15a of the outer tubular body 15 and the abutment seat 28. The lock pin 27, tightly fitted by the end member 17, thus prevents the relative axial slide between the outer tubular body 15, the inner tubular body 16 and the axial pin 24 in the locking region.
In a different embodiment, shown in figure 3, the lock pin, indicated hereinafter by reference numeral 27', extends through the outer tubular body 15, the inner tubular body 16 and the axial pin 24, thus preventing the relative axial slide in the locking region.
Furthermore, the constraint members comprise a lock ring 30, which is tightly fitted onto the outer tubular body 15 and is coupled to the end member 17 so as to prevent respective relative rotations between the outer tubular body 15 and the end member 17, thus preventing the release of the threaded coupling. For example, the lock ring 30 is provided with axial teeth which engage respective seats of the end member 17.
The flange 20 extends along axis A and has a through axial cavity 31 and a radial fluid passage 32, communicating with the axial cavity 31, for supplying fuel oil to the fluid delivery line 22. The axial cavity 31 ends with a neck 20a against which the end 15b of the outer tubular body 15 is arranged. The neck 20a and the end 15b of the outer tubular body 15 may be welded to each other. The end 16b of the inner tubular body 16 extends in the axial cavity 31 beyond the outer tubular body 15 and is inserted in a guide bushing 33, which belongs to the constraint members between the outer tubular body 15 and the inner tubular body 16. The guide bushing 33 supports the inner tubular body 16 in centered position on axis A and allows the axial slide thereof, in particular following the thermal expansion of the portion closest to the combustion chamber 2. Furthermore, the guide bushing 33 ensures fluid-tightness against the lateral wall of the inner tubular body 15, thus preventing leakage of fuel oil.
The flange 21 is coupled to the flange 20 and has a through axial cavity 35, communicating with the end 16b of the inner tubular body 16 through the guide bushing 33 to recover the fuel oil in excess coming from the fluid return line 23. The guide bushing 33 and the axial cavity 35 of the flange 21 define an expansion chamber which allow the free axial slide of the end 16b of the inner tubular body 16, which is free from axial constraints.
The described lance injector has many advantages. Firstly, one advantage derives from the fact that the relative axial slide constraint is closer to the hottest region of the injector in use, which is critical for the thermal and mechanical stresses and because the even partial obstruction of the fluid delivery and return lines must be avoided. The presence of the axial slide constraint causes the residual relative slide of the outer and inner tubular bodies and of the nozzle to be entirely negligible even following major differences of temperature. The opening of the fluid passages is thus ensured.
Furthermore, the outer and inner tubular bodies, which for their axial dimensions are subjected to higher expansions, are constrained to each other and to the end member without fitting, by inserting the lock pin and the threaded coupling between end member and outer tubular body. Consequently, there is no risk of damage or malfunctioning deriving from loss of interference between components.
Thus, with respect to the known injectors, the described lance injector is much less affected by the effects of the major thermal expansions caused by the high temperatures in the combustion chamber. The considerable robustness of the lance injector according to the invention allows, in turn, to reduce significantly the cooling air flow rate for correct operation during operation with gas supplied by the main burner and/or the pilot burner. The general efficiency general of the gas turbine is thus increased.
The correct positioning of the components may be maintained both in use (i.e. in presence of high temperatures and major temperature differences between the opposite ends of the outer and inner tubular bodies) and in rest conditions, without needing to resort to contrast elements tending to promote the restoring of a given configuration (for example, packs of Belleville washers operating against the ends of one or both the tubular bodies) . Thus, on one hand, the mechanical stresses and risks of failures are further reduced; on the other hand, the manufacturing of the lance injector is simplified.
Another advantage is given by the freedom of the outer and inner tubular bodies to expand in opposite direction with respect to the nozzle, where, by virtue of the chamber formed by the guide bushing and by the axial cavity, there are wide tolerances to allow relative axial slides without the risk of obstruction of passages and contact between various components. This aspect also contributes to reducing the risk of damage and malfunctions.
Finally, it is apparent that changes and variations may be made to the lance for injecting for fuel oil into a gas turbine combustion chamber without departing from the scope of protection of the present invention, as defined in the appended claims.

Claims

1) A lance injector for injecting fuel oil into a gas turbine combustion chamber (2), the lance injector comprising :
an outer tubular body (15) and an inner tubular body (16), which extend along a common axis (A) and define a first fluid line (22) in a gap between the outer tubular body (15) and the inner tubular body (16), and a second fluid line (23) in the inner tubular body (16); and
a nozzle (18) connected fluidically to the first fluid line (22) and to the second fluid line (23), at respective first ends (15a, 16a) of the outer tubular body (15) and the inner tubular body (16);
wherein the outer tubular body (15) and the inner tubular body (16) are constrained to each other by constraint members (17, 27, 27', 30, 33) so that the relative axial slide between the outer tubular body (15) and the inner tubular body (16) is prevented in a locking region at the respective first ends (15a, 16a), and is permitted on account of expansion, between the locking region and respective second ends (15b, 16b) opposite to the first ends (15a, 16a), of the outer tubular body (15) and the inner tubular body (16);
and wherein the constraint members (17, 27, 27', 30, 33) comprise a lock pin (27; 27') extending through the inner tubular body (16), crosswise to the axis (A), and projecting from the inner tubular body (16), the lock pin (27; 27') being connected to the inner tubular body (16) and to the outer tubular body (15) so as to prevent the relative axial slide between the outer tubular body (15) and the inner tubular body (16) in the locking region.
2) An injector as claimed in Claim 1, wherein the lock pin (27; 27') is perpendicular to the axis (A) .
3) An injector as claimed in Claim 1 or 2, wherein the constraint members (17, 27, 27', 30, 33) comprise an end member (17) fitted onto the first end (15a) of the outer tubular body (15) and configured to lock the lock pin (27; 27') axially with respect to the outer tubular body (15) .
4) An injector as claimed in Claim 3, wherein the end member (17) comprises an abutment seat (28), and is fitted to the first end (15a) of the outer tubular body (15) so as to clamp ends of the lock pin (27; 27') between an axial margin of the first end (15a) of the outer tubular body
(15) and the abutment seat (28) .
5) An injector as claimed in Claim 4, wherein the end member (17) and the first end (15a) of the outer tubular body (15) are connected by a threaded coupling.
6) An injector as claimed in Claim 5, wherein the constraint members (17, 27, 27', 30, 33) comprise a lock ring (30) tightly fitted to the outer tubular body (15) and coupled to the end member (17) so as to prevent rotation of the end member (17) about the outer tubular body (15) and release of the threaded coupling.
7) An injector as claimed in any one of Claims 3 to 6, wherein the end member (17) internally defines a fluid passage (29) between the first fluid line (22) and the nozzle ( 18 ) .
8) An injector as claimed in Claim 7, wherein the nozzle (18) comprises a lateral wall (26) defining a chamber (25) and having inlet openings for fluidly coupling the chamber (25) and the first fluid line (22) .
9) An injector as claimed in Claim 7 or 8, wherein the nozzle (18) and the end member (17) are connected interferentially, and the nozzle (18) projects axially outwards with respect to the end member (17) .
10) An injector as claimed in any one of the preceding Claims, comprising an axial pin (24), arranged in the inner tubular body (16) along the axis (A), facing the nozzle (18), and fitted through with the lock pin (27; 27') .
11) An injector as claimed in any one of the foregoing Claims, wherein the nozzle (18) has a supply outlet (25a) towards outside and a recovery outlet (25b) axially opposite the supply outlet (25a) and connected to the second fluid line (23) .
12) An injector as claimed in any one of the foregoing Claims, comprising an expansion chamber (35) configured to permit free axial slide of the second end (16b) of the inner tubular body (16) as a result of expansion.
13) An injector as claimed in any one of the foregoing Claims, wherein the constraint members (17, 27, 27', 30, 33) comprise a guide bushing (33) between the outer tubular body (15) and the inner tubular body (16), the guide bushing (33) being configured to permit axial slide of the inner tubular body (16) with respect to the outer tubular body (15) as a result of expansion.
14) A gas turbine burner comprising a lance injector (5) as claimed in any one of the foregoing Claims.
EP14796263.3A 2013-09-26 2014-09-26 Lance injector for injecting fuel oil into a gas turbine combustion chamber Active EP3049722B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT001592A ITMI20131592A1 (en) 2013-09-26 2013-09-26 LANCER INJECTOR FOR FUEL OIL INJECTION IN A GAS TURBINE COMBUSTION CHAMBER
PCT/IB2014/064867 WO2015044908A1 (en) 2013-09-26 2014-09-26 Lance injector for injecting fuel oil into a gas turbine combustion chamber

Publications (2)

Publication Number Publication Date
EP3049722A1 true EP3049722A1 (en) 2016-08-03
EP3049722B1 EP3049722B1 (en) 2019-08-21

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP14796263.3A Active EP3049722B1 (en) 2013-09-26 2014-09-26 Lance injector for injecting fuel oil into a gas turbine combustion chamber

Country Status (4)

Country Link
EP (1) EP3049722B1 (en)
CN (1) CN105637292B (en)
IT (1) ITMI20131592A1 (en)
WO (1) WO2015044908A1 (en)

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EP4187072B1 (en) 2021-11-26 2024-09-11 Ansaldo Energia Switzerland AG Fuel oil injector
CN115289471B (en) * 2022-08-12 2025-05-13 重庆博荣拓尔科技有限公司 Gas nozzle and gas nozzle structure of gas nail driver

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ITMI20101372A1 (en) * 2010-07-26 2012-01-27 Ansaldo Energia Spa METHOD AND EQUIPMENT TO DETECT LIQUID FUEL LEAKS IN A COMBUSTION GROUP OF A GAS TURBINE SYSTEM

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ITMI20131592A1 (en) 2015-03-27
CN105637292A (en) 2016-06-01
CN105637292B (en) 2017-11-10
WO2015044908A1 (en) 2015-04-02
EP3049722B1 (en) 2019-08-21

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