JP5693293B2 - Combustor - Google Patents

Description

  The present invention relates to a combustor constituting a gas turbine.

  A combustor constituting a gas turbine is provided in a passenger compartment of a compressor that generates compressed air, and generates high-temperature and high-pressure combustion gas by injecting fuel into the compressed air and burning it. And this combustor is arrange | positioned so that several may adjoin each other along the circumferential direction of the turbine to which combustion gas is supplied.

  Here, the combustor configured as described above has a plurality of acoustic modes coupled with the circumferential mode of the vehicle compartment, and if combustion vibration occurs in any of the acoustic modes, the combustor may be damaged. Cause. In view of this, it has been proposed in the past to reduce the acoustic coupling effect between the combustor and the passenger compartment by disposing an acoustic sleeve between the combustor and the passenger compartment (see, for example, Patent Document 1). ).

JP 2002-195565 A

  However, according to the conventional combustor, a plurality of combustors are arranged in the circumferential direction of the turbine, and these combustors are in close contact with each other in the circumferential direction through a narrow gap near the outlet of the combustion gas. Yes. Therefore, an acoustic mode in which a plurality of combustors are coupled exists due to the close relationship in the vicinity of the outlet (hereinafter referred to as “coupled mode”). In this coupled mode, resonance is also generated by an excitation force such as a vortex of combustion gas. However, no appropriate measures have been taken in the past for the resonance generated in the coupled mode between the combustors.

  The present invention has been made in consideration of such circumstances, and the purpose of the present invention is to generate resonance sound generated in a coupled mode between combustors for a plurality of combustors arranged in the circumferential direction of the turbine. It is to provide means for reducing.

  In order to achieve the above object, the present invention employs the following means. That is, the combustor according to the present invention has a cylindrical shape in which the fluid flowing in from one end side is combusted inside and flows out from the other end, and a plurality of the combustors are arranged in the vehicle interior so that the other end side is adjacent in the circumferential direction. A combustor body, and an acoustic tube provided in the vicinity of the fluid outlet of the combustor body so that a base end communicates with the combustor body.

  According to such a configuration, the acoustic tube is provided in the vicinity of the outlet that contributes to the combustor coupling, thereby changing the resonance frequency of the combustor in the coupled mode as compared with the case without the acoustic tube. Thereby, the resonance noise of the combustor generated in the coupled mode can be reduced under predetermined operating conditions.

  The combustor according to the present invention is characterized in that the acoustic tube is provided with an acoustic impedance variable mechanism that varies an acoustic impedance of the acoustic tube.

  According to such a configuration, the resonance frequency of the combustor in the coupled mode can be arbitrarily controlled by changing the acoustic impedance of the acoustic tube having frequency characteristics to a desired magnitude by the acoustic impedance variable mechanism. it can. Thereby, the resonance noise of the combustor generated in the coupled mode can be reduced under all operating conditions.

  Further, the combustor according to the present invention is characterized in that the acoustic impedance varying mechanism is a variable tube length mechanism that varies a tube length of the acoustic tube.

  According to such a configuration, the acoustic impedance of the acoustic tube can be changed to a desired magnitude by changing the tube length of the acoustic tube by the tube length variable mechanism.

  The combustor according to the present invention includes a tube length adjusting means in which the tube length varying mechanism has a cross-sectional shape substantially equal to that of the acoustic tube and is fitted therein, and the tube length adjusting means is connected to the acoustic tube. And moving means for moving the inside.

  According to such a configuration, the tube length adjusting means serves as a lid that seals the tip of the tube by fitting into the inside of the acoustic tube. The moving means moves the tube length adjusting means inside the acoustic tube, so that the tube length of the acoustic tube changes.

  Further, the combustor according to the present invention is characterized in that the moving means integrally moves the tube length adjusting means provided respectively in the plurality of acoustic tubes.

  According to such a configuration, since the moving means integrally moves the plurality of tube length adjusting means, the tube lengths of the plurality of acoustic tubes can be similarly changed. Thereby, since the acoustic impedance of a plurality of combustor bodies can be changed uniformly, the resonance frequency of the combustor in the coupled mode can be controlled more accurately and reliably.

  The combustor according to the present invention is characterized in that the acoustic impedance variable mechanism is a bleed mechanism for supplying a fluid into the acoustic tube.

  According to such a configuration, the acoustic impedance of the acoustic tube can be changed to a desired magnitude by supplying a fluid from the extraction mechanism and changing the temperature inside the acoustic tube.

  According to the combustor which concerns on this invention, the resonance sound which generate | occur | produces in the coupled mode of combustors can be reduced about the combustor arrange | positioned in the circumferential direction of a turbine.

It is a whole lineblock diagram showing the gas turbine which has a combustor concerning a 1st embodiment of the present invention. It is a schematic diagram which shows the state which looked at each combustor of 1st Embodiment from the exit part side. It is the partial expanded sectional view which expanded one of the combustors of a 1st embodiment. It is the elements on larger scale which expanded one of the combustors of 2nd Embodiment. It is a schematic diagram which shows the state which looked at each combustor of 2nd Embodiment from the exit part side.

(First embodiment)
Embodiments of the present invention will be described below with reference to the drawings. First, the configuration of the combustor according to the first embodiment of the present invention will be described. FIG. 1 is an overall configuration diagram showing a gas turbine 1 having a combustor 10 according to the present embodiment.

  The gas turbine 1 includes a compressor 2 provided at the most upstream position along the fluid flow direction F, a plurality of combustors 10 provided downstream of the compressor 2, and the combustors 10. And a turbine 3 provided on the downstream side.

  The compressor 2 takes in external air from the air intake 4 and compresses the air to generate compressed air. The combustor 10 generates high-temperature and high-pressure combustion gas by injecting fuel into the compressed air generated by the compressor 2 and burning it. Further, the turbine 3 extracts the driving force by converting the thermal energy of the combustion gas supplied from the combustor 10 into the rotational energy of the rotor 5. The driving force taken out by the turbine 3 is transmitted to a generator (not shown) connected to the rotor 5.

  Here, as shown in FIG. 1, the combustors 10 are arranged so that a plurality of the combustors 10 are adjacent to each other along the circumferential direction of the rotor 5. FIG. 2 is a schematic view showing a state in which each of the combustors 10 is viewed from the outlet portion 101, that is, the combustion gas outflow side. The plurality of combustors 10 are arranged so that their outlet portions 101 are in close contact with each other through a narrow gap C. The close relationship between the outlet portions 101 contributes to resonance in the combustor 10 in a coupled mode in which a plurality of combustors 10 are coupled to each other.

  FIG. 3 is a partially enlarged cross-sectional view in which one of the combustors 10 of the first embodiment is enlarged. The combustor 10 includes a cylindrical combustor main body 11 provided inside the casing 6 of the compressor 2, and a vicinity of an outlet portion 101 that is a downstream end of the combustor main body 11 and from which combustion gas flows out. And a tube length variable mechanism 13 (acoustic impedance variable mechanism) provided in the acoustic tube 12.

  As shown in FIG. 2, the combustor main body 11 is a cylindrical member and an inner cylinder 111 whose upstream end is fixed to the casing wall 7 of the compressor 2, and is also a cylindrical member. It has a tail cylinder 112 that connects the downstream end portion of the cylinder 111 to the combustion gas flow path 8 of the turbine 3, and a fuel nozzle 113 that is provided by being inserted into the tail cylinder 112.

  According to the combustor body 11 configured as described above, the compressed air generated by the compressor 2 is introduced into the inner cylinder 111, and mixing is performed by injecting fuel into the compressed air from the fuel nozzle 113. Gas is generated, and this gas mixture is combusted to generate combustion gas. Then, the combustion gas generated in the inner cylinder 111 is supplied to the combustion gas flow path 8 of the turbine 3 through the tail cylinder 112.

  The acoustic tube 12 is for changing the resonance frequency of the combustor body 11. As shown in FIG. 2, the acoustic tube 12 is provided with a tube-side flange 121 for fixing at the base end portion of a metal pipe having both ends opened, and the distal end thereof is bent by approximately 90 °. . The acoustic tube 12 configured as described above is fixed by bolting the tube side flange 121 against the tube side flange 102 provided so as to protrude from the outlet portion 101 of the combustor body 11. Thereby, the inside of the acoustic tube 12 and the inside of the combustor body 11 are in communication with each other. The acoustic tube 12 fixed to the combustor body 11 has a bent portion 122 at the tip thereof facing the circumferential direction of the turbine 3.

  Note that the material, shape, cross-sectional shape, longitudinal shape, number, and the like of the acoustic tube 12 are not limited to this embodiment, and can be appropriately changed in design. Moreover, the installation position of the acoustic tube 12 can be any position along the longitudinal direction of the combustor body 11, but in the vicinity of the outlet portion 101 that contributes to the coupling of the combustor 10 as in this embodiment. There is an advantage that the acoustic part is installed in the combustion unit 11 so that the resonance frequency of the combustor body 11 can be changed more accurately and reliably.

  The tube length variable mechanism 13 changes the tube length of the acoustic tube 12, that is, the length along the longitudinal direction. As shown in FIG. 2, the tube length varying mechanism 13 includes a moving means 131 provided so as to surround the plurality of combustors 10, a supporting means 132 fixed to the moving means 131, and an acoustic tube 12. And a pipe length adjusting means 133 that is provided and supported by the supporting means 132.

  The moving means 131 is for moving the tube length adjusting means 133. The moving means 131 can be rotated clockwise or counterclockwise around the combustor 10 by being driven to rotate by a motor or the like (not shown).

  The support means 132 is for supporting the tube length adjusting means 133. The support means 132 includes a fixing member 132a having one end fixed to the moving means 131 and extending in the radial direction of the rotor 5, and a support member 132b having one end fixed to the fixing member 132a and extending in the circumferential direction of the rotor 5. ,have.

  The tube length adjusting means 133 is for adjusting the tube length of the acoustic tube 12, that is, the length in the longitudinal direction. As shown in FIG. 3, the tube length adjusting means 133 has a cross-sectional shape substantially equal to the bent portion 122 at the distal end of the acoustic tube 12, and is fitted into the bent portion 122 so that the distal end of the acoustic tube 12 is fitted. It serves as a lid for sealing. The tube length adjusting means 133 is fixed to the other end portion of the support member 132b constituting the support means 132.

  Next, the effect of the combustor 10 which concerns on 1st Embodiment of this invention is demonstrated. The operation condition of the combustor 10 can be variously changed by changing a so-called pilot ratio, opening / closing timing of the air bypass valve, and the like. Here, when the combustor 10 is operated under predetermined operating conditions, resonance may occur in the combustor 10 in a coupled mode in which a plurality of combustors 10 are coupled together.

  In this case, the user of the combustor 10 reduces the resonance noise generated in the combustor 10 by changing the resonance frequency of the combustor 10 in the coupled mode by adjusting the tube length of the acoustic tube 12. More specifically, the user drives a motor (not shown) to rotate the moving means 131 shown in FIG. Then, the tube length of the acoustic tube 12 changes as the tube length adjusting unit 133 supported by the support unit 132 moves in the circumferential direction inside the acoustic tube 12. Specifically, when the moving unit 131 is rotated clockwise in FIG. 3, the tube length of the acoustic tube 12 becomes long as the tube length adjusting unit 133 moves inside the acoustic tube 12 toward the distal end opening side. . On the other hand, when the moving unit 131 is rotated counterclockwise in FIG. 3, the tube length adjusting unit 133 moves inside the acoustic tube 12 so as to be separated from the opening of the distal end, thereby shortening the tube length of the acoustic tube 12. Thus, when the tube length of the acoustic tube 12 changes, the acoustic impedance of the acoustic tube 12 changes, thereby changing the resonance frequency of the combustor 10 in the coupled mode.

  Further, as the moving means 131 rotates, the tube length adjusting means 133 provided in each of the plurality of acoustic tubes 12 moves integrally, so that the tube lengths of the plurality of acoustic tubes 12 similarly change. Thereby, since the acoustic impedance of the plurality of combustor bodies 11 can be changed uniformly, the resonance frequency of the combustor 10 in the coupled mode can be controlled more accurately and reliably.

(Second Embodiment)
Next, the configuration of the combustor according to the second embodiment of the present invention will be described. In addition, about the whole structure of the gas turbine which has a combustor which concerns on this embodiment, and structures other than a combustor, since it is the same as 1st Embodiment, description is abbreviate | omitted here.

  4 and 5 are views showing the configuration of the combustor 20 according to the second embodiment. FIG. 4 is a partially enlarged cross-sectional view of one of the combustors 20, and FIG. It is a schematic diagram which shows the state seen from the exit part 201, ie, the side from which combustion gas flows out.

  As shown in FIGS. 4 and 5, the combustor 20 according to the second embodiment includes a cylindrical combustor main body 11 provided inside the casing 6 of the compressor 2, and an outlet portion of the combustor main body 11. The acoustic tube 21 provided in the vicinity of 201 and the extraction mechanism 22 (acoustic impedance variable mechanism) provided in the acoustic tube 21 are provided. Since the configuration of the combustor body 11 is the same as that of the first embodiment, the same reference numerals as in FIG. 3 are given in FIG. 4 and the description thereof is omitted here.

  The acoustic tube 21 is different from the acoustic tube 12 of the first embodiment in which the proximal end portion is opened but the distal end portion is closed and both ends are opened. About another structure, it is the same as that of the acoustic tube 12 of 1st Embodiment.

  The bleed mechanism 22 is for controlling the temperature inside the acoustic tube 21. As shown in FIGS. 4 and 5, the bleed mechanism 22 has an air delivery means 221 capable of delivering air, one end connected to the air delivery means 221, and the other end inserted through the distal end of the acoustic tube 21. Then, the air supply pipe 222 introduced into the inside and the temperature control means 223 for controlling the temperature of the air supplied to the acoustic pipe 21 are provided.

  Next, the effect of the combustor 20 which concerns on 2nd Embodiment of this invention is demonstrated. When the combustor 20 of the present embodiment is also operated under predetermined operating conditions, resonance may occur in the combustor 20 in a coupled mode in which a plurality of combustors 20 are coupled together.

  In this case, the user of the combustor 20 reduces the resonance sound generated in the combustor 20 by changing the resonance frequency of the combustor 20 in the coupled mode by adjusting the temperature inside the acoustic tube 21. Let More specifically, the user supplies air to the inside of the acoustic tube 21 by operating the air delivery means 221 and adjusts the temperature of the supplied air to a predetermined temperature by the temperature control means 223. If it does so, the resonance frequency of the combustor 20 in a coupled mode will change by the temperature inside the acoustic tube 21 changing, and the acoustic impedance changing.

  The various shapes, combinations, operation procedures, and the like of the constituent members shown in the above-described embodiments are merely examples, and various changes can be made based on design requirements and the like without departing from the gist of the present invention.

DESCRIPTION OF SYMBOLS 1 Gas turbine 2 Compressor 3 Turbine 4 Air intake port 5 Rotor 6 Car interior 7 Car interior wall 8 Combustion gas flow path 10 Combustor 11 Combustor body 12 Acoustic pipe 13 Variable pipe length mechanism 20 Combustor 21 Acoustic pipe 22 Extraction mechanism 101 outlet portion 102 cylinder side flange 111 inner cylinder 112 tail cylinder 113 fuel nozzle 121 pipe side flange 122 bent portion 131 moving means 132 support means 133 pipe length adjusting means 201 outlet part 221 air delivery means 222 air supply pipe 223 temperature control means 132a fixed Member 132b Support member C Gap F Flow direction

Claims (6)

A combustor main body that has a cylindrical shape that flows out from the other end after the fluid flowing in from the one end side is combusted inside, and is disposed in a plurality so that the other end side is adjacent in the circumferential direction in the vehicle interior;
An acoustic tube provided in the vicinity of the fluid outlet of the combustor body so that a base end communicates with the combustor body;
A combustor comprising:   The combustor according to claim 1, wherein the acoustic tube is provided with an acoustic impedance variable mechanism that varies an acoustic impedance of the acoustic tube.   The combustor according to claim 2, wherein the acoustic impedance variable mechanism is a variable tube length mechanism that varies a tube length of the acoustic tube.   The tube length varying mechanism has a cross-sectional shape substantially equal to that of the acoustic tube, and is provided by fitting inside the tube length adjusting unit, and a moving unit for moving the tube length adjusting unit inside the acoustic tube. The combustor according to claim 3, wherein the combustor is provided.   The combustor according to claim 4, wherein the moving unit integrally moves the tube length adjusting unit provided in each of the plurality of acoustic tubes.   The combustor according to claim 2, wherein the acoustic impedance variable mechanism is an extraction mechanism that supplies a fluid to the inside of the acoustic tube.

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