WO2019107392A1

WO2019107392A1 - Combustor and gas turbine

Info

Publication number: WO2019107392A1
Application number: PCT/JP2018/043723
Authority: WO
Inventors: 貴也甲田; 敬介松山; 友仁中森; 佐藤　賢治; 剣太郎徳山; 裕行武石; 健太谷口
Original assignee: 三菱日立パワーシステムズ株式会社
Priority date: 2017-11-29
Filing date: 2018-11-28
Publication date: 2019-06-06
Also published as: JP2019100583A; JP6978912B2

Abstract

The present invention comprises: a cylindrical combustion tube (21) through which a combustion gas (B) flows; an introduction pipe (41) connected to the outer peripheral surface of the combustion tube (21) such that one end of the introduction pipe (41) communicates with the interior of the combustion tube (21); an acoustic space formation part (32) connected in a communicating manner to the other end of the introduction pipe (41), an acoustic space being formed in the acoustic space formation part (32); and a connection part (51) provided between the one end of the introduction pipe (41) and the combustion tube (21), the inner surface of the connection part (51) being continuous with an inner peripheral surface (21A) of the combustion tube (21), and the diameter of the connection part (51) decreasing in a convex-curved-surface shape toward the introduction pipe (41).

Description

Combustor and gas turbine

The present invention relates to a combustor and a gas turbine.
Priority is claimed on Japanese Patent Application No. 2017-229553, filed Nov. 29, 2017, the content of which is incorporated herein by reference.

The combustor which comprises a gas turbine is provided in the vehicle interior inside into which the compressed air produced | generated by the compressor is introduce | transduced. The combustor generates high-temperature and high-pressure combustion gas inside a cylindrical combustion cylinder. A plurality of combustors are disposed adjacent to each other in the circumferential direction of the turbine to which the combustion gas is supplied.

For example, Patent Document 1 discloses a technology for suppressing combustion vibration generated during operation of a combustor by attaching an acoustic damper to the combustor.

Patent No. 5693293 gazette

Here, in the combustion cylinder, air column resonance may occur in which the upstream end of the flow of combustion gas is opened and the downstream end serving as the outlet connected to the turbine is closed. When such air column resonance occurs, combustion oscillations of an acoustic mode in which a plurality of combustors are coupled to one another via respective outlets are generated.

The present invention provides a combustor and a gas turbine that can effectively suppress combustion vibration based on air column resonance.

The combustor according to the first aspect of the present invention includes a cylindrical combustion cylinder through which combustion gas flows, and an introduction pipe connected to an outer peripheral surface of the combustion cylinder such that one end thereof communicates with the inside of the combustion cylinder. An acoustic space forming part connected to the other end of the introduction pipe in a communicating state to form an acoustic space inside, and provided between one end of the introduction pipe and the combustion cylinder, the inner surface is the combustion cylinder An acoustic device having a connecting portion which is continuous with the inner circumferential surface of the connecting portion and whose diameter is reduced in a convex curved shape toward the introduction pipe.

Here, air column resonance in the combustion cylinder of the combustor occurs according to the following principle. A traveling wave traveling downstream in the combustion cylinder is reflected at the downstream end of the combustion cylinder. As a result, a reflected wave that travels in the reverse direction of the traveling wave, that is, the upstream side is generated inside the combustion cylinder. Thus, the reflection at the downstream end of the combustion liner occurs because the acoustic impedances of the combustor and the turbine are different. The greater the difference between the two impedances, the greater the energy of the reflected wave. Then, the air column resonance is generated by the interference between the reflected wave and the traveling wave.
In the present invention, an acoustic device is provided in communication with the combustion cylinder. By providing such an acoustic device, the acoustic impedance of the entire combustor can be adjusted. As a result, the difference between the acoustic impedance of the turbine and the acoustic impedance of the combustor as a whole can be reduced, and the generation of a reflected wave that causes the air column resonance can be suppressed.

Here, if the separation of the combustion gas occurs temporarily at the connection point between the combustion cylinder and the acoustic device and the flow is greatly disturbed, that is, if an eddy current occurs, the acoustic impedance at the connection point is greatly increased. . This increases the difference between the acoustic impedance of the entire combustor and the acoustic impedance of the turbine. As a result, the energy of the reflected wave at the downstream end of the combustion cylinder becomes large, and air column resonance occurs largely.
On the other hand, in the present invention, the connection point with the combustion cylinder in the acoustic impedance is a connection part having a convex curved surface on the inner surface side. By this, it can suppress that the combustion gas in a combustion pipe | tube peels in a connection location with an acoustic device. For this reason, it can be avoided that the acoustic impedance of the entire combustor deviates largely from the intended value. As a result, it is possible to suppress an increase in the reflected wave generated in the combustion cylinder.

Further, in the above-described combustor, the curvatures of the convex curved surfaces on the inner surface of the connection portion may be different between the downstream side and the upstream side in the flow direction of the combustion gas.

According to this configuration, it is possible to control the amount of heat and dynamic pressure received by the downstream side of the flow direction of the combustion gas, particularly of the connection portion, and to suppress overheating of the portion.

Further, in the above-described combustor, the center of curvature of the convex curved surface on the inner surface downstream of the flow direction of the combustion gas of the connection portion is upstream in the cross-sectional view of the surface including the central axis of the introduction pipe of the connection portion. It may be provided in the diameter direction outside of the above-mentioned combustion pipe rather than the curvature center of the convex curve in the inside of the side.

According to this configuration, it is possible to more effectively control the amount of heat and dynamic pressure received by the downstream side of the flow direction of the combustion gas, particularly in the connection portion, and to suppress overheating of the portion.

Further, the above-described combustor may have a protruding portion which is raised toward a central axis of the combustion cylinder on a part of a convex curved surface on the inner surface of the connection portion.

According to this configuration, it is possible to suppress the overheating of the portion by creating a flow that avoids the collision of the connection portion particularly toward the downstream side of the flow direction of the combustion gas.

Also, the combustor has a radius of curvature r ₁ of the convex curved surface in the connecting portion inner surface, the radius r ₀ of the inner diameter of the inlet tube, in the relationship represented by 3r _₀ ≧ r ₁ ≧ 0.2r ₀ It is also good.

According to this configuration, it is possible to more effectively suppress the generation of the eddy current in the vicinity of the connection portion due to the separation.

Further, the above-mentioned combustor is an ellipse having a circular shape or a long axis extending in any direction along the inner surface of the combustion cylinder when viewed in the central axis direction of the introduction pipe, and the radius of the circular shape or the oval and _{r 2} is in the form of the long axis radius, the radius _{r 0} of the inner diameter of the inlet pipe, may be in a relationship represented by 4r ₀ ≧ _{r 2} ≧ _{r 0.}

According to this configuration, the generation of the eddy current in the vicinity of the connection portion due to the separation is more effectively suppressed.

Also, the combustor has a projected area A ₁ in the central axis direction as viewed in the inlet pipe of the connecting portion, and the inner area A ₀ of the inlet tube, represented by 12A ₀ ≧ A ₁ ≧ A ₀ It may be in a relationship.

A gas turbine according to the present invention includes a compressor that generates high pressure air, a combustor having any of the above-described configurations, and a turbine driven by the combustion gas.

According to the present invention, combustion vibration based on air column resonance can be effectively suppressed.

It is a longitudinal section of a gas turbine which has a burner concerning a first embodiment of the present invention. It is a fragmentary sectional view of a burner concerning a first embodiment of the present invention. It is a longitudinal cross-sectional view containing the central axis of the introductory pipe of the principal part in the burner concerning a first embodiment of the present invention. FIG. 3 is a view in the direction of the central axis line of the introduction pipe of the main part of the combustor according to the first embodiment of the present invention. It is a longitudinal cross-sectional view containing the central axis of the introductory pipe of the principal part in the burner concerning a second embodiment of the present invention. It is a longitudinal cross-sectional view containing the central axis of the introductory pipe of the principal part in the burner concerning a third embodiment of the present invention.

First Embodiment
Hereinafter, a combustor 11 according to a first embodiment of the present invention will be described in detail with reference to the drawings.
First, the configuration of the gas turbine 1 according to the first embodiment of the present invention will be described. FIG. 1 is an overall configuration view shown as a longitudinal cross-sectional view of a gas turbine 1 having a combustor 11 according to the present embodiment.

The gas turbine 1 includes a compressor 4 provided at an upstream position along a flow direction F in which the fluid flows, and a plurality of combustors 11 provided downstream of the compressor 4. And a turbine 5 provided downstream of the combustor 11 and operatively coupled to the compressor. A plurality of combustors 11 are disposed adjacent to each other along the circumferential direction of the rotor 6.

The compressor 4 takes in external air from the air intake port 7 and compresses the air to generate compressed air. The compressor 4 has a compressor rotor 14 extending along the gas turbine rotation axis O1, and a compressor casing 24 covering the compressor rotor from the outer peripheral side. The compressor rotor 14 has a substantially cylindrical shape with the gas turbine rotation axis O1 as a central axis. A compressor moving blade 34 is attached to the outer peripheral surface between the outer peripheral surface of the compressor rotor 14 and the inner peripheral surface of the compressor casing 24. The compressor moving blades 34 are configured as a moving blade row formed by attaching a plurality of pieces on the outer peripheral surface of the compressor rotor 14 along the circumferential direction. Furthermore, on the compressor rotor 14, a plurality of moving blade rows are disposed at intervals in the fluid flow direction along the direction of the rotation axis O1. A compressor stator blade 44 is attached to the inner peripheral side of the compressor casing 24. The compressor stator blades 44 are configured as a stator blade row in which a plurality of compressor stator blades 44 are attached to the inner circumferential surface of the compressor casing 24 along the circumferential direction. Furthermore, on the inner peripheral surface of the compressor casing 24, a plurality of stator blade rows are disposed at intervals in the fluid flow direction along the axial direction of the compressor rotor 14. The stationary blade rows are arranged so as to alternate with the moving blade rows in the direction of the gas turbine rotation axis O1.
Although FIG. 1 shows an example in which six rows of moving blade rows and six rows of stationary blade rows are provided, the number of moving blade rows and fixed blade rows is not limited thereto.

The combustor 11 generates a high temperature and high pressure combustion gas flow B by injecting fuel to the compressed air generated by the compressor 4 and burning it.
Further, the turbine 5 receives the combustion gas flow B supplied from the combustor 11 and converts it into rotational energy of the rotor 6 to extract driving force. The turbine 5 has a turbine rotor 15 extending along the gas turbine rotation axis O1, and a turbine casing 25 covering the turbine rotor from the outer peripheral side. The configuration of the turbine 5 is similar to that of the compressor 4. That is, the turbine rotor 15 has a substantially cylindrical shape whose center axis is the gas turbine rotation axis O1. A turbine blade 35 is attached to the outer peripheral surface between the outer peripheral surface of the turbine rotor 15 and the inner peripheral surface of the turbine casing 25. The turbine moving blades 35 are configured as a moving blade row formed by mounting a plurality of pieces on the outer peripheral surface of the turbine rotor 15 along the circumferential direction. Furthermore, on the turbine rotor 15, a plurality of moving blade rows are disposed at intervals in the fluid flow direction along the direction of the rotation axis O1. A turbine stator blade 44 is attached to the inner circumferential side of the turbine casing 25. The turbine stator blade 45 is configured as a stator blade row in which a plurality of turbine stator blades 45 are attached to the inner circumferential surface of the turbine casing 25 along the circumferential direction. Furthermore, on the inner peripheral surface of the turbine casing 25, a plurality of stator blade cascades are disposed at intervals in the fluid flow direction along the axial direction of the turbine rotor 15. The stationary blade rows are arranged so as to alternate with the moving blade rows in the direction of the gas turbine rotation axis O1. Although FIG. 1 shows an example in which four rows of moving blade rows and four rows of stationary blade rows are provided, the number of moving blade rows and fixed blade rows is not limited to this.

Here, the operation of the turbine 5 configured as described above will be described. The high-temperature, high-pressure combustion gas flow B generated by the combustor flows toward the flow direction F while accelerating at the same time as the turbine 5 expands, and the turbine stator blades 45 (the stator blade row) and the turbine blades 35 Pass through (moving blade row) sequentially. The turbine stator 45 rectifies the gas flow. In response to the rectified combustion gas flow B, the turbine blades 35 convert kinetic energy in the flow direction F of the combustion gas flow B into rotational movement of the turbine rotor 15 about the gas turbine rotation axis O1. In the present embodiment, the turbine rotor 15 shares the rotational axis O1 with the compressor rotor 14 and is interlockably coupled. Therefore, the rotational force of the rotating turbine rotor 15 is immediately transmitted to the coaxial compressor rotor 14 and the compressor rotor 14 is rotated. The compressor rotor 14 rotates the compressor moving blades 34 around the rotation axis O1 to allow the air taken from the outside inside the compressor 4 to be compressed by the moving blades 34 (moving blade row) and the compressor stationary blades 44 The stator blade row is sent in the flow direction F while being compressed while sequentially passing through. The high pressure compressed air thus generated is mixed with the fuel in the combustor 11 to become a high temperature / high pressure combustion gas flow B, and flows to the turbine 5. Further, the rotational force generated as described above is transmitted to the generator 20 connected to the rotor 6 to generate electric power. In addition, although the example which provided the generator 20 coaxially with the rotor 6 is shown in FIG. 1, the generator 20 does not necessarily need to be provided coaxially with the rotor 6. FIG. The rotational force of the rotor 6 may be transmitted to the generator 20 by a gear mechanism or the like.

Next, the configuration of the combustor 11 according to the first embodiment of the present invention will be described. FIG. 2 is a partially enlarged cross-sectional view of one of the combustors 11 of the first embodiment. The combustor 11 is provided with a cylindrical combustion cylinder 21 provided inside the casing 8 of the gas turbine 1 and an acoustic device 31 provided in the middle of the combustion cylinder 21.
The combustion cylinder 21 has a tubular shape whose cross-sectional shape gradually changes from a cylindrical shape to a rectangular shape as it goes downstream. The downstream end (combustion gas outlet) of the combustion cylinder 21 is connected to the turbine 5. A combustion region of combustion gas is formed in the combustion cylinder 21. The combustion area of the combustion gas is generated by burning the fuel ejected by the pilot nozzle and the main nozzle by compressed air.
The acoustic device 31 includes an acoustic chamber 32, an introduction pipe 41, and a connection portion 51. As an example, in the present embodiment, the introduction pipe 41 is cylindrical. At the end of the introduction tube 41, a cylindrical acoustic chamber 32 having an inner diameter larger than its inner diameter is provided. The introductory pipe 41 and the acoustic chamber 32 share a central axis on the introductory pipe central axis O3. At the end of the cylindrical acoustic chamber 32 on the side where the introduction pipe 41 exists, a member made of the same material as the member forming the cylindrical shape covers the opening end of the introduction pipe 41 on the acoustic chamber 32 side without closing it. There is. That is, the introduction pipe 41 communicates with the end of the acoustic chamber 32. In particular, in the present embodiment, as an example, the end of the introduction pipe 41 extends to the inside of the acoustic chamber 32. On the other hand, the end on the side not connected to the introduction pipe 41 is closed by a member made of the same material as the member forming the cylindrical shape. In other words, the acoustic chamber 32 has a sealed structure except for one end where the introduction pipe 41 is in communication. The space inside the enclosed acoustic chamber 32 is an acoustic space R.
One end of the introduction pipe 41 is connected in communication with the inside of the combustion cylinder 21 via the connection portion 51. The connection portion 51 is also a tube diameter expansion portion of the introduction tube 41. The connection portion 41 has a substantially cylindrical shape sharing a central axis with the introduction pipe 41. The portion where the connection portion 51 and the introduction pipe 41 are connected is formed to be smoothly connected. The tube diameter expansion from the introduction tube 41 to the connection portion 51 is stepless in the central axis direction. In that point, it differs from the part to which the introductory pipe 41 and the acoustic chamber 32 are connected. The connection portion of the connection portion 51 to the combustion cylinder 21 is preferably a portion including the combustion region of the combustion cylinder 21 or a portion downstream of the combustion region.
With the above configuration, the acoustic space R is connected to the space inside the combustion cylinder 21 via the space inside the introduction pipe 41. Moreover, as for the acoustic device of the said structure, all of the acoustic chamber 32, the introductory tube 41, and the connection part 51 are circular in cross section, and are cylindrical shapes which share a central axis. Therefore, it is possible for the entire device to vibrate evenly in the circumferential direction. Furthermore, it is advantageous in terms of strength because there are few places where stress concentration occurs. The structure about the part to which the connection part 51 and the combustion pipe | tube 21 are connected is mentioned later.

Hereinafter, the principal part of the combustor 11 according to the first embodiment of the present invention will be described in detail. FIG. 3 is a longitudinal cross-sectional view of the periphery of the connection portion 51, including the central axis O3 of the introduction pipe 41 which is the central axis of the introduction pipe 41. In the present embodiment, the connecting portion inner surface 51A, which is the inner surface of the connecting portion 51, is connected to the combustion cylinder inner surface 21A, which is the inner peripheral surface of the combustion cylinder 21, and the inner peripheral surface 41A, which is the inner peripheral surface of the inlet pipe 41 The diameter is reduced in a convex curved surface shape toward the pipe 41.
The connection portion 51 is a member separate from the combustion cylinder 21 and the introduction pipe 41. The connection portion 51 is made of, for example, metal of the same material as the introduction pipe 41, and is joined to the combustion cylinder 21 and the introduction pipe 41 by welding. Here, an overlap portion 51 B with the combustion cylinder 21 is provided at the peripheral edge portion of the end portion of the connection portion 51 on the side connected to the combustion cylinder 21. The overlap portion 51B is a peripheral portion of the end portion of the connection portion 51 connected to the combustion cylinder 21 and is formed by cutting only the inner peripheral surface side over the entire circumference only a predetermined distance from the peripheral edge ing. The connection portion 51 is provided such that the overlap portion 51B is in contact with the outer surface of the combustion cylinder 21. Here, in the overlap portion 51B in the present embodiment, the depth of the notch (that is, the radial length of the combustion cylinder 21 when assembled to the combustion cylinder 21) is a wall constituting the combustion cylinder 21. Equal to the thickness of With this configuration, it is possible to secure the strength of the connection portion while connecting the inner peripheral surface of the connection portion 51 and the inner surface of the combustion cylinder 21 in a smooth connection. Further, with this configuration, the connection portion 51 (or the entire acoustic device 31) can be easily assembled from the outside of the combustion cylinder 21. Furthermore, since the positioning operation at the time of assembly becomes easy, the workability is improved. Furthermore, in the present embodiment, as an example, the notches are not formed in the combustion cylinder 21 and the notches are provided only in the peripheral portion of the connecting portion 51 which is relatively thick. This, in addition to the above-mentioned advantages, does not generate a special operation process other than opening the holes for the combustion cylinder which has already been assembled. Therefore, it is also advantageous in terms of working because an acoustic device can be attached.

With the above configuration, the inner surface of the connection portion 51 is connected to the inner surface of the combustion cylinder 21. In other words, the connection portion inner surface 51A and the combustion cylinder inner surface 21A are formed as a smooth integral curved surface. At this time, the curved surface is a curved surface convex toward the inner surface of the connection portion 51 in a cross-sectional view of the surface including the axial center of the introduction tube 41 of the connection portion 51. Subsequently, the shape of the convex curved surface will be described in detail.

Convex surface of curvature radius r ₁ of the connecting portion inside surface 51A in the combustor 11 according to the first embodiment of the present invention, as an example, compared to the radius r ₀ of the inner diameter of the inlet pipe _{_{41, 3r 0 ≧ r 1 ≧}} 0. it may be set within a range of a relation represented by 2r _0. Further, the size of the connection portion 51 is, for example, as an outline shown in FIG. 4 as a contour of a portion of the connection portion 51 excluding the overlap portion 51B in the axial direction of the introduction pipe 41 from the inside of the combustion cylinder 21. a connecting portion 51 radius r ₂ is the radius of the circle, the radius r ₀ of the inner diameter of the inlet pipe 41 may be set within a range of a relation represented by 4r ₀ ≧ r ₂ ≧ r _0. In the present embodiment, the cross section of the connection portion 51 is circular, but the connection portion 51 may have a cylindrical shape which gradually deforms from circular to elliptical toward the side connected to the combustion cylinder 21. In this case, the connection portion 51 radius r _2, the long axis radius of惰円as the contour of the portion excluding the overlapping portion 51B of the connecting portion 51 in the axial direction as viewed in the introduction pipe 41 from the interior of the combustion cylinder 21 It may be At this time, the major axis of the oval may extend in any direction along the inner surface of the combustion cylinder. Furthermore, the size of the connection portion 51 is, for example, the connection portion 51 projected area A ₁ which is the area of the introduction tube 41 in the axial direction, and the inner area A ₀ of the introduction tube 41: 12A ₀ AA ₁ it may be set within a range of a relation represented by ≧ a _0. Here, the inner area A ₀ means the area of a region surrounded by an axial view which has the inner circumferential surface of the introduction pipe 41 as a contour.

In the combustor 11 configured as described above, the connection portion inner surface 51A and the combustion cylinder inner surface 21A are formed into a smooth integral curved surface. Therefore, the combustion gas flow B can flow while bending relatively gently along the connecting portion upstream convex curved surface 51Aa, which is the upstream convex curved surface of the connecting portion 51. Thereby, the combustion gas flow in the vicinity of the introduction pipe combustion cylinder side end 41 B which is the combustion cylinder 21 side end of the introduction pipe 41 is rectified. Therefore, the dissipation of the sound energy due to the turbulent flow is suppressed, and the rise of the acoustic impedance in the vicinity of the connection portion 51 can be suppressed.

Here, if the acoustic impedance in the vicinity of the connection portion 51 largely increases, the acoustic impedance of the entire combustor 11 increases. As a result, the difference in acoustic impedance between the entire combustor 11 and the turbine 5 becomes large. For this reason, the energy of the reflected wave generated at the downstream end of the combustion cylinder 21 is increased based on the traveling wave traveling downstream in the combustion cylinder 21. As a result, the interference between the reflected wave and the traveling wave is increased, and the air column resonance is largely generated.

On the other hand, in the present embodiment, as described above, it is possible to suppress the separation of the combustion gas in the vicinity of the connection portion 51 between the acoustic device 31 and the combustion cylinder 21. Therefore, it is possible to suppress that the acoustic impedance of the entire combustor 11 is largely deviated from the intended value. Therefore, the downstream end of the combustion liner 21 can be brought close to the non-reflecting boundary. As a result, it is possible to avoid an increase in the reflected wave generated in the combustion cylinder 21 and to suppress an increase in air column resonance. Therefore, the combustion vibration which generate | occur | produces by couple | bonding a several combustor 11 can be suppressed.

The acoustic device 31 also functions as a Helmholtz resonance type acoustic damper. In the present embodiment, an increase in acoustic impedance in the vicinity of the connection portion 51 between the acoustic device 31 and the combustion cylinder 21 can be suppressed. Therefore, the acoustic energy in the combustion liner 21 can be effectively introduced into the acoustic device 31. By this, the muffling function as an acoustic damper can be exhibited effectively.

Moreover, the radius of curvature _{r 1} of the convex curved surface of the connecting portion 51, as compared to the radius _{r 0} of the inner diameter of the inlet pipe 41, satisfy the relation represented by _{_{_{3r 0 ≧ r 1 ≧ 0.2r 0}}} . As a result, the combustion gas flow can be controlled by the convex curved surface with an appropriate curvature in consideration of the combustion gas flow velocity and pressure. For this reason, while having the curvature necessary to rectify the combustion gas flow B in the vicinity of the end of the introduction pipe 41 on the side of the combustion cylinder 21, the structure of the minimum size can be obtained.

Further, the size of the connection portion 51 is, for example, the radius of the circle when the connection portion 51 is circular in the axial direction view of the introduction tube 41, or is elliptical when the same direction view and elliptic r ₂ is a circular long axis radius, and the radius r ₀ of the inner diameter of the inlet pipe 41 is defined within a range where the relation represented by 4r ₀ ≧ r ₂ ≧ r _0. As a result, the connecting portion 51 can be configured to have a size necessary to rectify the combustion gas flow B in the vicinity of the end of the introduction pipe 41 on the side of the combustion cylinder 21.

Furthermore, as an example of the size of the connection portion 51, the connection portion projection area A1 in the axial direction view of the introduction tube 41 and the inner area A ₀ of the introduction tube 41 are represented by 12A ₀ AA ₁ AA ₀ Defined within the scope of As a result, the connecting portion 51 can be configured to have a size necessary to rectify the combustion gas flow B in the vicinity of the end of the introduction pipe 41 on the side of the combustion cylinder 21.

Second Embodiment
Next, a second embodiment will be described with reference to FIG. In the second embodiment, the same components as those of the first embodiment are denoted by the same reference numerals and the detailed description thereof is omitted.
The second embodiment is different from the first embodiment in the configuration of the connection portion 52.
In the present embodiment, the curvature of the convex curved surface in the connection portion inner surface 52A has a smaller value as it goes downstream in the flow direction of the combustion gas. That is, as it goes to the circulation direction downstream of the combustion gas, it has a gentle curved surface. As an example, in the radius of curvature rr, the downstream convex curved surface radius of curvature rr2, which is the radius of curvature downstream of the flow direction of the combustion gas flow B, is larger than the upstream convex curved surface radius of curvature rr1 which is the upstream radius of curvature. It has become.

Further, in the present embodiment, the positions of the curvature centers Or of the convex curved surfaces in the connection portion inner surface 52A are different from each other on the upstream side and the downstream side in the flow direction of the combustion gas flow B. In the present embodiment, among the curvature centers Or, the downstream convex curved surface curvature center Or2 that is the curvature center downstream of the combustion gas flow B in the flow direction is more than the upstream convex curved surface curvature center Or1 that is the upstream curvature center The combustion cylinder 22 is positioned radially outward.

In the combustor 12 having the above configuration, it is possible to relatively reduce the dynamic pressure of the combustion gas flow B received by the connecting portion downstream convex surface 52Ab, which is the flow direction downstream side of the combustion gas flow, among the connection portions 52. . More specifically, as described above, the combustion gas flow B is led to the introduction pipe 42 side along the connecting portion upstream convex surface 52Aa which is the curved surface on the upstream side of the connecting portion 52 in the flow direction. . Here, on the downstream side, a flow of returning the combustion gas flow B led to the introduction pipe 42 side by the connection portion downstream convex surface 52Ab with the above configuration to the combustion cylinder 22 side is created. As compared with the first embodiment, the connecting portion downstream side convex curved surface 52Ab in the present embodiment is located further downstream in the gas flow direction, and exists radially outward of the combustion cylinder 22, and is more gentle. It is a convex surface. As a result, the combustion gas flow B flows on the surface of the portion lying more toward the combustion cylinder inner surface 22A in the connecting portion downstream convex surface 52Ab. As a result, the concentration of collisions with respect to the connecting portion downstream side curved surface 52Ab is alleviated. Therefore, overheating and stress concentration of the portion can be suppressed, and the reliability of the combustor 12 can be enhanced.

Third Embodiment
Next, a third embodiment will be described with reference to FIG. In the third embodiment, the same components as those of the first embodiment are denoted by the same reference numerals and the detailed description thereof is omitted.
The third embodiment is different from the first embodiment in the configuration of the connection portion 53.
In the present embodiment, the connecting portion 53 is provided with a convex curved surface raised portion 63 in which a part of the convex curved surface is raised in the direction of the central axis O2 of the combustion cylinder 23 on the inner surface on the upstream side in the combustion gas flow direction. In the present embodiment, as an example, the convex curved surface raised portion 63 is formed as a thick portion of the connection portion 53.

In the combustor 13 configured as described above, the combustion gas flow B is led to the introduction pipe 43 side along the upstream convex curved surface 53Aa of the connection portion as described above. Here, by the convex curved surface protruding portion 63 on the upstream side in the flow direction of the combustion gas flow B in the connection portion 53 having the above configuration, it is once guided inward in the radial direction of the combustion cylinder 23. The combustion gas flow B introduced in this manner is led outward in the combustion cylinder radial direction by the connecting portion upstream convex surface 53Aa. Therefore, the combustion gas flow B passing near the connection portion 53 can flow relatively inward in the combustion cylinder radial direction.
Further, the combustion gas flow B is directed in the circumferential direction of the combustion cylinder 23 so as to avoid the protrusion by the convex curved surface raised portion 63 on the upstream side of the flow direction of the combustion gas flow B in the connection portion 53 with the above configuration. Become.
By the above-described operation, concentration of collision on the downstream convex surface 53Ab of the connection portion is alleviated. Therefore, overheating and stress concentration of the portion can be suppressed, and the reliability of the combustor can be enhanced. In addition, it is formed as a thick portion of the connection portion 53. Therefore, it is advantageous in terms of strength, and the above effect can be obtained without increasing the number of special parts.

The first, second, and third embodiments of the present invention have been described in detail with reference to the drawings, but the specific configuration is not limited to this embodiment, and the scope without departing from the scope of the present invention And design changes etc. are also included.
For example, although the acoustic device 31 includes the box-shaped acoustic chamber 32, the acoustic device 31 may have a cylindrical shape provided by being wound in the circumferential direction of the combustion cylinder.
Moreover, although the convex-curved convex part 63 in 3rd embodiment presupposed that it is formed as a part of the thickness of the connection part 53, it is not restricted to this. For example, even in the vicinity of the convex curved surface protuberance, the thickness may be the same as the thickness of the member constituting the other connection portion 53.

1, 2, 3

Gas turbines

11, 12, 13 Combustor 4 Compressor 14 Compressor rotor 24 Compressor casing 34 Compression blade 44 Compressor vane 5 Turbine 15 Turbine rotor 25 Turbine casing 35 Turbine bucket 45 Turbine vane 6 Rotor 7 Air intake port 8

compartments

21, 22, 23

combustion cylinders

21A, 22A, 23A,
Combustion cylinder inner surface 31 Acoustic device 32

Acoustic chamber

41, 42, 43

Introduction tube

41A, 42A, 43A Introduction tube inner circumferential surface 41B Introduction tube combustion

tube side end

51, 52, 53

Connection

51A, 52A Connection inner surface 51Aa Connection upstream Side convex curved surface 52Aa Connection portion upstream convex surface 52Ab Connection portion downstream convex surface 53Ab Connection portion downstream convex surface 51B Overlap portion 63 convex curved surface raised portion F fluid flow direction B combustion gas flow R acoustic space r ₁ , rr convex curved surface radius a ₁ connecting portion projected area a ₀ introducing tube area O1 gas turbine rotation axis O2 combustion tube central axis O3 introducing tube central axis Or convex curved center of curvature Or1 upstream-side convex of the inner diameter of the curvature radius r ₂ connecting portion radius r ₀ inlet tube Curved surface curvature center Or2 downstream convex Surface curvature center rr1 upstream convex curved surface curvature radius rr2 downstream convex curved surface curvature radius

Claims

A cylindrical combustion cylinder through which combustion gas flows,
An introduction pipe connected to the outer peripheral surface of the combustion cylinder so that one end is in communication with the inside of the combustion cylinder, and an acoustic space formed in the inside of which an acoustic space is formed by being connected to the other end of the introduction pipe in communication. And a connecting portion provided between one end of the introduction pipe and the combustion cylinder, the inner surface being continuous with the inner circumferential surface of the combustion cylinder and having a diameter decreasing toward a convex curved surface toward the introduction pipe An acoustic device,
A combustor comprising:
The combustor according to claim 1, wherein the curvatures of the convex curved surface on the inner surface of the connection portion are different between the flow direction downstream of the combustion gas and the upstream side.
The center of curvature of the convex curved surface on the inner surface of the connecting portion on the downstream side of the flow direction of the combustion gas is the curvature of the convex curved surface on the upstream side in a sectional view of the surface including the central axis of the introducing pipe of the connecting portion. The combustor according to claim 1, wherein the combustor is provided radially outward of the combustion cylinder than a center.
The combustor according to claim 1, further comprising: a protruding portion protruding toward a central axis of the combustion cylinder on a part of a convex curved surface on the inner surface of the connection portion.
The radius of curvature r 1 of the convex curved surface in the connection portion inner surface, the radius r 0 of the inner diameter of the inlet tube, the combustor according to claim 1 having a relationship represented by 3r 0 ≧ r 1 ≧ 0.2r 0 .
The connecting portion is circular as viewed in the central axis direction of the introduction tube, or elliptical with a long axis extending in any direction along the inner surface of the combustion cylinder, and the radius of the circular or the long axis radius of the oval r The combustor according to claim 1, wherein 2 and the radius r 0 of the inner diameter of the introduction pipe are in a relationship represented by 4 r 0 rr 2 rr 0 .
The projected area A 1 of the connection portion in the central axis direction of the introduction pipe and the inner area A 0 of the introduction pipe are in a relationship represented by 12A 0 AA 1 AA 0. Burner.
A compressor that produces compressed air;
A combustor according to any one of claims 1 to 7;
A turbine driven by the combustion gas;
A gas turbine equipped with