JP2004076601A - Turbine stationary blade structure - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide new stationary blade structure suited for incorporation into a turbine, even if a main body of the stationary blade, a outer shroud and an inner shroud are not integrated. <P>SOLUTION: Instead of conventional turbine stationary blade structure that has an annular sectional gas passage around a turbine shaft, this invention presents the outer shroud with inner peripheral surface forming an outer periphery of the gas passage, the inner shroud with outer peripheral surface forming an inner periphery of the gas passage, and the stationary blade that is a long member sandwiched between the outer shroud and the inner shroud, with longitudinal axis extended in the radial direction, and cross sectional envelope of an airfoil shape. One end of the stationary blade is fitted into or fixed to either of the outer shroud or the inner shroud, and the other end of the stationary blade abuts to the other of the inner shroud or the outer shroud and at least slides freely in the turbine shaft direction. <P>COPYRIGHT: (C)2004,JPO

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a turbine vane structure. In particular, the present invention relates to a gas turbine stationary blade structure which is characterized by a stationary blade supporting structure and a cooling structure and is suitable for a ceramic stationary blade.
[0002]
[Prior art]
Turbines are used as power generators and aircraft propulsion. Combustion gases and high temperature steam flow through the gas passages of the turbine. The gas passage is a space sandwiched between the outer shroud and the inner shroud. In the gas passage, moving blades and stationary blades are alternately arranged along the turbine shaft method.
Increasing the turbine inlet gas temperature can improve turbine output and energy efficiency. Generally, the inlet gas temperature of the turbine (for example, 1300 ° C.) is determined by the strength of the material of the components forming the gas passage in a high-temperature environment.
In recent years, in order to make the inlet gas temperature higher (for example, 1600 ° C.), ceramic moving blades, stationary blades, outer shrouds, and inner shrouds having higher strength in a high-temperature environment than metal are employed.
The casing that forms the external appearance of the turbine and the bearing box that supports and supports the turbine shaft are conventionally made of metal because the operating temperature is lower than the internal temperature of the gas passage.
The blades, vanes, outer shroud and inner shroud made of ceramic are mounted on their casings or bearings via metallic components (eg, an outer metal ring supporting the outer shroud and an inner metal ring supporting the inner shroud). Supported by a box.
[0003]
When the turbine is switched from the stopped state to the operating state, the temperature of the gas passage changes from room temperature to a high temperature. The temperature of the components constituting the turbine changes from room temperature to the temperature in each steady state.
Since the thermal expansion coefficients of the materials of the components are different, when the components are thermally expanded, the casing or the bearing housing becomes large in the radial direction, whereas the ceramic moving blade, the stationary blade, the outer shroud and The dimensions of the inner shroud hardly expand.
Conventionally, since the stationary blade structure that supports both ends of the stationary blade is adopted, in order to absorb the difference in dimensional change due to thermal expansion between the ceramic stationary blade and metal parts, the stationary blade supporting structure Special measures were taken.
[0004]
Hereinafter, a typical support structure of a conventional stationary blade support structure will be described with reference to the drawings. FIG. 7 is a conventional structural diagram.
The turbine vane structure 2 includes a vane 91, an outer metal ring 92, an outer thin plate 93, a mounting bolt 94, an outer spring 95, an outer mounting bolt 96, an inner metal ring 97, an inner spring 98, and an inner mounting bolt 99. Is done.
The stationary blade 91 is made of ceramic, and the stationary blade main body, the outer shroud, and the inner shroud are integrated. Generally, such a stationary blade 91 is manufactured by sintering ceramic powder.
[0005]
The outer metal ring 92 is fixed to the casing 3 of the turbine and supports the outer shroud portion of the stationary blade 91.
The outer thin plate 93 is fixed to the outer metal ring 92, and fixes one end of a mounting bolt 94 described later. The outer thin plate 93 has a thin plate structure, and easily undergoes out-of-plane deformation within the elastic region by the pulling force of the mounting bolt 94.
The mounting bolt 94 restricts the movement of the stationary blade 91 in the radial direction. One end is fixed to the outer thin plate 93 and the other end is fixed to an inner metal ring 97 described later.
The outer spring 95 is a member that urges the outer metal ring 92 to one side along the turbine axial direction.
The outer mounting bolt 96 is a member that fixes the outer metal ring 92 to the casing 3. The outer metal ring 92 is guided in the turbine axial direction by outer mounting bolts 96, and is urged in one direction by an outer spring 95.
[0006]
The inner metal ring 97 is fixed to the bearing housing 4 and supports the inner shroud portion of the stationary blade 91. The part of the inner metal ring 97 to which the mounting bolt 94 is mounted has a thin plate structure, and easily undergoes out-of-plane deformation within the elastic region due to the pulling force of the mounting bolt 94.
The inner spring 98 is a member that urges the inner metal ring 97 to one side along the turbine axis.
The inner mounting bolt 99 is a member that fixes the inner metal ring 97 to the bearing housing 4. The inner metal ring 97 is guided in the turbine axial direction by an inner mounting bolt 99, and is urged in the other direction by an inner spring 98.
[0007]
Therefore, the stationary blade 91, the outer metal ring 92, and the inner metal ring 97 are positioned in the radial direction by the mounting bolt 94, and are positioned in the turbine axial direction by the outer spring 95 and the inner spring 98.
When the temperature of the turbine rises from room temperature to the operating temperature, even if there is a difference in the dimensional change due to the thermal expansion of the outer metal ring 92, the inner metal ring 97, and the stationary blade 91 of the casing 3, the bearing housing 4, the outer thin plate in the radial direction. 93 and the inner metal ring 97 are elastically deformed, and the outer spring 95 and the inner spring 98 are elastically deformed in the turbine axial direction, thereby preventing a large thermal distortion from occurring.
[0008]
[Problems to be solved by the invention]
In recent years, attempts have been made to further increase the temperature of the gas passage of the turbine.
As one of the methods, adoption of a stationary blade having a structure in which a plurality of types of ceramics are mixed and monocrystallized is being studied. A stationary blade having this structure has high strength at high temperatures, and can be used even at a temperature of, for example, 1600 ° C.
However, the manufacturing technique of the stator vane having this structure is still under study, and at present, a structure having a complicated bent portion cannot be manufactured. The stator vane body, the outer shroud, and the inner shroud become separate bodies.
Therefore, in the vane where the stator vane body, the outer shroud, and the inner shroud are separate, a new vane structure that allows the vane to be incorporated into the turbine using the conventional turbine vane structure has been developed. It was expected.
[0009]
The present invention has been devised in view of the above-described problems, and replaces a conventional vane structure of a turbine having a gas passage having an annular cross section around a turbine shaft, and includes a vane main body and an outer shroud. Even if the inner shroud is not a unitary structure, it seeks to provide a new vane structure suitable for incorporation into a turbine.
[0010]
[Means for Solving the Problems]
In order to achieve the above object, a turbine vane structure having a gas passage having an annular cross section around a turbine shaft according to the present invention includes an outer shroud having an inner peripheral surface forming an outer periphery of the gas passage, and an outer peripheral surface having an outer peripheral surface. An inner shroud forming an inner periphery of a gas passage, and a stationary blade that is a long member having a cross-section in which an envelope extends in a radial direction and a longitudinal axis extends between the outer shroud and the inner shroud in a radial direction, Wherein one end of the vane fits or is fixed to one of an outer shroud or an inner shroud, and the other end of the vane abuts the other of the outer shroud or the inner shroud and at least in the turbine axial direction. It is slidable.
[0011]
According to the configuration of the present invention, the inner peripheral surface of the outer shroud forms the outer periphery of the gas passage, the outer peripheral surface of the inner shroud forms the inner periphery of the gas passage, and the envelope has a wing-shaped cross section. A stator vane, which is a member, is sandwiched between the outer shroud and the inner shroud and extends a longitudinal axis in a radial direction, and one end of the stator vane is fitted or fixed to one of the outer shroud or the inner shroud, Since the other end of the vane abuts on the other of the outer shroud or the inner shroud and is slidable at least in the turbine axial direction, the position of the outer shroud and the position of the inner shroud are different from the turbine shaft. , The other end of the vane in contact with the other of the outer shroud or the inner shroud is slidable in the turbine axial direction, and Stator blades structure composed of Udo and said inner shroud and the vanes are maintained.
[0012]
Further, it is preferable that the turbine vane structure according to the present invention includes a radial urging means for urging the outer shroud and the inner shroud in a direction to approach each other.
According to the configuration of the present invention, since the radial urging means urges the outer shroud and the inner shroud in the approaching direction, the position of the outer shroud and the position of the inner shroud change along the radial direction. Even so, the other end of the stationary blade continues to contact the other of the outer shroud or the inner shroud, and the stationary blade structure including the outer shroud, the inner shroud, and the stationary blade is maintained.
[0013]
Furthermore, the turbine vane structure according to the present invention includes an outer metal ring fixed to a casing of the turbine, the outer shroud includes a pair of front and rear outer grooves provided around the turbine axis, and It is preferable that the metal ring has a pair of front and rear outer claw portions that gently engage with the outer groove portions.
According to the configuration of the present invention, the pair of front and rear outer claw portions of the outer metal ring fixed to the casing of the turbine gently engage with the outer groove portions provided on the outer shroud. The amount of heat that propagates through the groove and the outer claw portion and moves to the outer metal ring can be reduced, and the temperature of the outer metal ring can be reduced.
[0014]
Further, in the turbine vane structure according to the present invention, it is preferable that the outer metal ring has a plurality of protrusions that come into contact with the outer peripheral portion of the outer shroud.
According to the configuration of the present invention, since the plurality of protrusions of the outer metal ring abut on the outer peripheral portion of the outer shroud, the amount of heat transferred from the outer shroud to the outer metal ring through the protrusion is reduced. And the temperature of the outer metal ring can be reduced.
[0015]
Further, in the turbine vane structure according to the present invention, the outer metal ring has an outer cooling gas hole, and the cooling gas is sandwiched between the outer metal ring and the outer shroud from the outer cooling gas hole. It is preferable that the gas enters the gap and blows out to the gas passage from the gap where the outer groove and the outer claw are engaged.
According to the configuration of the present invention, the cooling gas enters the gap between the outer metal ring and the outer shroud from the outer cooling gas hole, and the gas flows from the gap in which the outer groove and the outer claw engage. Since the gas is blown into the passage, the cooling gas can gas-cool the outer metal ring and lower the temperature of the outer metal ring.
[0016]
Further, the turbine vane structure according to the present invention includes an inner metal ring fixed to a bearing housing of the turbine, the inner shroud includes a pair of front and rear inner grooves provided around the turbine axis, Preferably, the inner metal ring has a pair of front and rear inner claws that gently engage the inner groove.
According to the configuration of the present invention, the pair of front and rear inner claw portions of the inner metal ring fixed to the bearing housing of the turbine are gently engaged with the inner groove portions provided in the inner shroud. The amount of heat transferred to the inner metal ring by heat propagation between the inner groove and the inner claw can be reduced, and the temperature of the inner metal ring can be reduced.
[0017]
Further, in the turbine vane structure according to the present invention, it is preferable that the inner metal ring has a plurality of protrusions that come into contact with an inner peripheral portion of the inner shroud.
According to the configuration of the present invention, since the plurality of protrusions of the inner metal ring abut on the inner peripheral portion of the inner shroud, the amount of heat that propagates from the inner shroud to the protrusion and moves to the inner metal ring is reduced. And the temperature of the inner metal ring can be reduced.
[0018]
Further, in the turbine vane structure according to the present invention, the inner metal ring has an inner cooling gas hole, and cooling gas is sandwiched between the inner metal ring and the inner shroud from the inner cooling gas hole. It is preferable that the gas is blown into the gas passage from the gap where the inside groove portion and the inside claw portion are engaged.
According to the configuration of the present invention, the cooling gas enters the gap between the inner metal ring and the inner shroud from the inner cooling gas hole, and the gas flows from the gap in which the inner groove and the inner claw are engaged. Since the cooling gas is blown into the passage, the cooling gas can gas-cool the inner metal ring and lower the temperature of the inner metal ring.
[0019]
Furthermore, in the turbine vane structure according to the present invention, it is preferable that the radial urging means is a corrugated spring provided on an outer peripheral portion of the outer shroud or an inner peripheral portion of the inner shroud.
According to the configuration of the present invention, since the radial urging means is a corrugated spring, the vane can be urged toward the other end with a simple and lightweight structure.
[0020]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. In each of the drawings, common portions are denoted by the same reference numerals, and redundant description is omitted. FIG. 1 is a side sectional view of an embodiment according to the present invention. FIG. 2 is an AA sectional view of the embodiment according to the present invention. FIG. 3 is a sectional view taken along line BB of the embodiment according to the present invention. FIG. 4 is a sectional view taken along the line CC of the embodiment according to the present invention. FIG. 5 is a sectional view taken along line DD of the embodiment according to the present invention. FIG. 6 is an EE cross-sectional view of the embodiment according to the present invention.
For convenience of description, in FIG. 1, the left hand side as viewed in the drawing is the front of the turbine shaft, and the right hand side is the rear of the turbine shaft as viewed. The gas flows through the gas passage 5 from the front to the rear.
[0021]
The turbine vane structure 2 is a structure for assembling the vanes inside the turbine 1 and the vanes, and includes a vane 10, an outer shroud 20, an outer metal ring 30, a radial corrugated spring 40 (radial urging means). ), An outer turbine axial corrugated spring 50, an inner shroud 60, an inner metal ring 70, and an inner turbine axial corrugated spring 80. The turbine 1 has a gas passage 5 having an annular cross section around a turbine shaft 6.
[0022]
The stator vane 10 is a ceramic member whose longitudinal axis extends in the radial direction and is sandwiched between an outer shroud 20 and an inner shroud 60, which will be described later. It is composed only of A plurality of vane bodies 11 are arranged in the radial direction.
The fitting protrusion 14 is provided at an outer end (corresponding to one end) of the stationary blade main body 11. The fitting protrusion 14 fits into a fitting recess 24 of the outer shroud 20 described later. FIGS. 1 and 2 show a state in which the fitting projection 14 is fitted into the fitting recess 24. The fitting projection 14 has a shape in which the leading edge and the trailing edge of the blade section of the stationary blade body 11 are cut off.
The inner end 12 (corresponding to the other end) of the stator vane main body 11 has an end face that crosses in the longitudinal direction and is parallel to the outer peripheral surface 62 of the inner shroud main body 61 facing the same.
The inner end portion 12 of the stator vane 10 is urged by a radial corrugated leaf spring 40 described later to abut an outer peripheral surface 62 of an inner shroud body 61 described later, and is slidable at least in the turbine axial direction. I have.
[0023]
The outer shroud 20 is a ceramic member whose inner peripheral surface 22 forms the outer periphery of the gas passage 5. The outer shroud 20 has a substantially cylindrical shape surrounding the outside of the gas passage 5 and is composed of a plurality of outer shroud bodies 21 divided in a circumferential direction. Generally, it is divided according to the number of the stationary blades 10.
A fitting recess 24 is provided on the inner peripheral surface 22 of the outer shroud main body 21 so that the fitting projection 14 of the stationary blade main body 11 fits.
A pair of front and rear outer grooves 23 are provided on the outer shroud 20 around the turbine axis. FIG. 1 shows an outer groove 23 provided horizontally on the front end face and the rear end face of the outer shroud main body 21.
[0024]
The outer metal ring 30 is a metal member fixed to the casing 3 of the turbine. The outer metal ring 30 has a substantially annular shape surrounding the outer periphery of the outer shroud 20, and includes a plurality of outer metal ring bodies 31 divided in a circumferential direction. A pair of front and rear outer claw portions 32 are provided on the outer metal ring 30 so as to gently engage with the outer groove portions 23. The front outer claw 32 is engaged with the front outer groove 22, and the rear outer claw 32 is engaged with the rear outer groove 22. A substantially annular gap (hereinafter, referred to as an outer gas seal chamber F1) is formed at a position between the inner peripheral portion of the outer metal ring 30 and the outer peripheral portion of the outer shroud 20.
Further, an outer cooling gas hole 33 is provided in a wall of the outer metal ring 30 facing the outer gas seal chamber F1. The cooling gas introduced into the inside of the casing 3 enters the outer gas seal chamber F1 from the outer cooling gas hole 33, and blows out to the gas passage 5 from the gap where the outer groove 23 and the outer claw 32 are engaged.
Outer metal ring mounting bolts 35 penetrate through elongated holes 34 provided in casing 3 at three locations on the outer peripheral portion of outer metal ring 30 to fix casing 3 and outer metal ring 30. The long holes 34 are provided at locations of the casing 3 that are equally spaced around the turbine shaft 6. The longitudinal direction of the long hole 34 is along the radial direction.
[0025]
The radial corrugated leaf spring 40 is a functional component that urges the outer shroud 20 and the inner shroud 60 in a direction toward each other. The radial corrugated plate spring 40 is an annular spring member that is undulating and undulates, and is wound around the outer periphery of the outer shroud 20. FIGS. 1 and 3 show a corrugated spring accommodated in the outer gas seal chamber F1 and having an outer periphery in contact with the inner periphery of the outer metal ring main body 31 and an inner periphery in contact with the outer periphery of the outer shroud main body 21. It is shown. The outer shroud body 31 and the outer metal ring body 31 sandwich and elastically deform the radial corrugated plate spring 40, and the generated elastic force pushes the outer shroud body 21 toward the inner shroud body 61.
[0026]
The outer turbine axial corrugated spring 50 is a functional component that urges the outer shroud 20 in a direction along the turbine axis. The outer turbine axial direction corrugated plate spring 50 is a spring member that is undulating and has a flange shape and is provided at the front end of the outer shroud main body 21. 1 and 4 show an outer turbine axial corrugated spring 50 sandwiched between an outer metal ring main body 31 and an outer shroud 21. The outer metal ring main body 31 and the outer shroud 21 sandwich the outer turbine axial corrugated spring 50, and the generated elastic force pushes the outer shroud main body 21 rearward along the turbine axis.
[0027]
The inner shroud 60 is a ceramic member whose outer peripheral surface forms the inner periphery of the gas passage 5. The inner shroud 60 has a substantially cylindrical shape surrounding the inside of the gas passage 5 and is constituted by a plurality of inner shroud bodies 61 divided in a circumferential direction, so that disassembly and assembly are facilitated. Generally, it is divided according to the number of the stationary blades 10.
A pair of front and rear inner grooves 63 are provided in the inner shroud 60 along the turbine axis. FIG. 1 shows an inner groove 63 provided horizontally on the front end face and the rear end face of the inner shroud main body 61.
[0028]
The inner metal ring 70 is a metal member fixed to the bearing housing 4 of the turbine. The inner metal ring 70 has a substantially annular shape surrounding the inner periphery of the inner shroud 60 from the inside, and includes a plurality of inner metal ring bodies 71 divided in the circumferential direction. A pair of front and rear inner claws 72 are provided on the inner metal ring 70 so as to gently engage with the inner groove 63. The front inner claw 72 engages with the front inner groove 62, and the rear inner claw 72 engages with the rear inner groove 62. A substantially annular gap (hereinafter, referred to as an inner gas seal chamber F2) is formed at a position between the outer peripheral portion of the inner metal ring 70 and the inner peripheral portion of the inner shroud 60.
Further, an inner cooling gas hole 73 is provided in a wall of the inner metal ring 70 facing the inner gas seal chamber F2. The cooling gas introduced into the bearing housing 4 enters the inner gas seal chamber F2 from the inner cooling gas hole 73 and blows out to the gas passage 5 from the gap where the inner groove 63 and the inner claw 72 are engaged.
Further, a plurality of inner protrusions 74 are provided on a surface of the inner metal ring 70 that contacts the inner gas seal chamber F2. The tip of the inner protrusion 74 is in contact with the inner peripheral portion of the inner shroud 60. FIGS. 1 and 5 show four inner projections 74 abutting on the inner peripheral portion of the inner shroud main body 61.
[0029]
The inner turbine axial corrugated spring 80 is a functional component that urges the inner shroud 60 in a direction along the turbine axis. The inner turbine axial direction corrugated spring 80 is a spring member which is undulating and has a flange shape and is provided at the front end of the inner shroud main body 61. FIGS. 1 and 5 show an inner turbine axial corrugated spring 80 sandwiched between an inner metal ring body 71 and an inner shroud 61. The inner metal ring main body 71 and the inner shroud main body 61 sandwich the inner turbine axial corrugated spring 80, and the generated elastic force pushes the inner shroud main body 61 rearward along the turbine axis.
[0030]
Next, the operation of the turbine vane support structure according to the embodiment of the present invention will be described.
At first, the turbine is at rest, and the temperature of each member constituting the turbine 1 is close to room temperature.
The stationary blade 10 is fitted to the outer shroud main body 21 to form an integral structure. A radial corrugated spring 40 pushes the unitary structure toward the inner shroud body 61. The other end 12 of the stationary blade 10 is pressed against the outer peripheral surface 62 of the inner shroud 60 and positioned.
An outer turbine axial corrugated spring 50 biases the outer shroud 20 rearwardly along the turbine axis. The outer shroud body 21 is pressed against the outer metal ring body 31 and positioned.
An inner turbine axial corrugated spring 80 biases the inner shroud 60 rearwardly along the turbine axis. The inner shroud body 61 is pressed against the inner metal ring body 71 and positioned.
[0031]
When the turbine is in operation, high-temperature gas (combustion gas, high-temperature steam, etc.) flows into the gas passage.
Since the inner peripheral surface 22 of the stationary blade 10 and the outer shroud 20 and the outer peripheral surface 62 of the inner shroud 30 are in direct contact with the high-temperature gas, the temperature of the stationary blade 10, the outer shroud 20 and the inner shroud 30 becomes It approaches the temperature of the gas.
The cooling gas introduced into the inside of the casing 3 enters the outer gas sealing chamber F1 from the outer cooling gas hole 33 and blows out to the gas passage 5 from the gap where the outer groove 23 and the outer claw 32 are engaged. As the cooling gas cools the outer metal ring 30, the temperature of the outer metal ring 30 will be lower than the temperature of the hot gas. By adjusting the flow rate of the cooling gas, the temperature of the outer metal ring 30 becomes a value suitable for maintaining the sufficient high-temperature strength of the outer metal ring 30.
The cooling gas introduced into the bearing housing 4 enters the inner gas seal chamber F2 from the inner cooling gas hole 73 and blows out to the gas passage 5 from the gap where the inner groove 63 and the inner claw 72 are engaged. As the cooling gas cools the inner metal ring 70, the temperature of the inner metal ring 70 will be lower than the temperature of the hot gas. By adjusting the flow rate of the cooling gas, the temperature of the inner metal ring 70 becomes a value suitable for maintaining sufficient high-temperature strength of the inner metal ring 70.
[0032]
The casing 3, the outer metal ring 30, the inner metal ring 70, and the bearing housing 4 are made of a material having substantially the same coefficient of thermal expansion, and the size of each member increases as the temperature rises. For example, the distance between the outer metal ring 30 and the inner metal ring 70 increases by about 1 mm.
On the other hand, since the materials of the stationary blade 10, the outer shroud 20, and the inner shroud 60 are made of a material (for example, ceramics) having an extremely small coefficient of thermal expansion as compared with metal, a dimensional change due to thermal expansion is small. A radial corrugated spring 40 pushes the vane 10 and the outer shroud 20 toward the inner shroud 60. The other end 12 of the stationary blade 10 is moved by being pressed against the outer peripheral surface 62 of the inner shroud 60 and positioned.
The positions of the outer metal ring 30 and the inner metal ring 70 in the turbine axial direction are shifted by, for example, about 1 mm. Outer turbine axial corrugated spring 50 urges outer shroud 20 in a direction along the turbine axis, and inner turbine axial corrugated spring 80 urges inner shroud 60 in a direction along the turbine axis. Since the other end 12 of the stationary blade 10 is slidable at least in the turbine axial direction, abnormal thermal distortion does not occur in the stationary blade 10, the outer shroud 20, and the inner shroud 60.
Since the outer metal ring 30 is fixed on its outer periphery by three outer metal ring mounting bolts 35, the outer metal ring 30 moves through the elongated hole 34 by the size of thermal expansion and is automatically centered on the turbine shaft center.
[0033]
By using the turbine vane structure of the above-described embodiment,
When the turbine enters the operating state from the rest state and the temperature of each member constituting the turbine reaches a steady temperature, even if the relative positions of the outer shroud and the inner shroud in the turbine axial direction are deviated, the other end of the stationary blade is not affected. No abnormal thermal stress occurs on the stator vanes and inner shroud because the outer surface of the section and the inner shroud slide in the turbine axial direction. Further, a good stationary blade support structure can be maintained, and the performance of the turbine can be maintained.
In addition, since the radial corrugated spring urges the stator blade toward the inner shroud, even if the relative positions of the outer shroud and the inner shroud in the radial direction are misaligned, the other end of the stator blade and the inner shroud may be displaced. A gap with the outer peripheral surface is not opened, a good stationary blade support structure can be maintained, and the performance of the turbine is not affected. Further, no abnormal thermal stress is generated in the stationary blade and the inner shroud.
Also, since the claw structure of the outer metal ring or the inner metal ring is loosely engaged with the groove structure of the outer shroud or the inner shroud, the outer metal ring or the inner metal ring can loosely support the outer shroud or the inner shroud, In addition, since the propagation of heat in the groove and the claw portion is suppressed, the heat of the outer shroud or the inner shroud is less likely to be transmitted to the outer metal ring or the inner metal ring, and the temperature of the outer metal ring or the inner metal ring does not rise, so that the casing or The temperature of the bearing box does not rise.
In addition, since the plurality of protrusions of the inner metal ring abut on the inner peripheral portion of the inner shroud, the propagation of heat at the contact portion of the protrusion can be suppressed, and the heat of the inner shroud propagates to the inner metal ring. And the temperature of the inner metal ring does not rise, nor does the temperature of the casing or bearing housing.
In addition, since the cooling gas is passed through the outer gas seal chamber and the inner gas seal chamber and blown out to the gas passage, the outer metal ring and the inner metal ring can be gas-cooled, and the temperature of the outer metal ring and the inner metal ring can be reduced. Can be lowered.
Further, since the radial corrugated spring 40 (radial urging means), the outer turbine axial corrugated spring, or the inner turbine axial corrugated spring has a corrugated structure, the structure of the urging means is simplified, Further, since the heat propagation of the corrugated sheet is suppressed, the heat of the outer shroud or the inner shroud is less likely to be transmitted to the outer metal ring or the inner metal ring through the corrugated sheet, and the temperature of the outer metal ring or the inner metal ring is reduced. The temperature of the casing or the bearing housing does not rise.
[0034]
The present invention is not limited to the embodiments described above, and various changes can be made without departing from the gist of the invention.
Although one end of the stationary blade has been described as being fitted to the outer shroud, the present invention is not limited to this. For example, if it can be manufactured, the stationary blade and the outer shroud may be integrated.
Further, the outer end of the stationary blade is fitted to the outer shroud so as to be slidable between the inner end of the stationary blade and the inner shroud, but is not limited thereto. The end may be fitted to the inner shroud to allow sliding between the outer end of the vane and the outer shroud.
Further, the radial corrugated plate spring is wound around the outer peripheral portion of the outer shroud, but is not limited thereto. For example, it may be wound around the inner peripheral portion of the inner shroud.
[0035]
【The invention's effect】
As described above, the vane structure of the turbine having the gas passage having the annular cross section around the turbine shaft according to the present invention has the following effects due to its configuration.
Since the end of the vane abuts on the other of the outer shroud or the inner shroud and is slidable in the turbine axial direction, the position of the outer shroud and the position of the inner shroud change along the turbine axis. Also, the other end of the vane in contact with the other of the outer shroud or the inner shroud is slidable in the turbine axial direction, and the vane includes the outer shroud, the inner shroud, and the stator vane. The structure is maintained.
Also, since the radial biasing means biases the outer shroud and the inner shroud in a direction to approach, the position of the outer shroud and the position of the inner shroud change along the radial direction. Also, the other end of the stationary blade continues to contact the other of the outer shroud or the inner shroud, and the stationary blade structure including the outer shroud, the inner shroud, and the stationary blade is maintained.
Further, since the coupling structure between the outer shroud and the outer metal ring is an engagement structure of a groove and a claw, heat is propagated from the outer shroud to the outer groove and the outer claw to the outer metal ring. The amount of heat transferred can be reduced, and the temperature of the outer metal ring can be reduced.
Further, since the plurality of protrusions of the outer metal ring are configured to abut on the outer peripheral portion of the outer shroud, it is possible to reduce the amount of heat that propagates from the outer shroud to the protrusion and moves to the outer metal ring. The temperature of the outer metal ring can be reduced.
Further, since the cooling gas is caused to pass through the gap between the outer metal ring and the outer shroud, the cooling gas can cool the outer metal ring and lower the temperature of the outer metal ring.
Further, since the coupling structure between the inner shroud and the inner metal ring is an engagement structure of a groove and a claw, heat is propagated from the inner shroud to the inner groove and the inner claw to the inner metal ring. The amount of heat transferred can be reduced, and the temperature of the inner metal ring can be reduced.
In addition, since the plurality of protrusions of the inner metal ring abut on the outer peripheral portion of the inner shroud, the amount of heat that propagates from the inner shroud to the protrusion and moves to the inner metal ring can be reduced. The temperature of the inner metal ring can be reduced.
Further, since the cooling gas is caused to pass through the gap between the inner metal ring and the inner shroud, the cooling gas can cool the inner metal ring and lower the temperature of the inner metal ring.
Further, since the radial urging means is a corrugated spring, the stationary blade can be urged toward the other end with a simple and lightweight structure.
Therefore, even when the stationary blade main body, the outer shroud, and the inner shroud are not integrated, a stationary blade structure suitable for being incorporated in a turbine can be provided.
[0036]
[Brief description of the drawings]
FIG. 1 is a side sectional view of an embodiment according to the present invention.
FIG. 2 is an AA sectional view of the embodiment according to the present invention.
FIG. 3 is a BB cross-sectional view of the embodiment according to the present invention.
FIG. 4 is a sectional view taken along the line CC of the embodiment according to the present invention.
FIG. 5 is a sectional view taken along line DD of the embodiment according to the present invention.
FIG. 6 is an EE cross-sectional view of the embodiment according to the present invention.
FIG. 7 is a conventional structural view.
[Explanation of symbols]
F1 Outer gas seal chamber
F2 Inner gas seal chamber
1 turbine
2 Stator structure
3 Casing
4 Bearing housing
5 Gas passage
6 Turbine shaft
10 Stationary wing
11 Stationary wing body
12 The other end
13 One end
14 Fitting projection
20 Outer shroud
21 Outer shroud body
22 Inner circumference
23 Outer groove
24 Fitting recess
30 Outer metal ring
31 Outer metal ring body
32 Outside claw
33 Outside cooling gas hole
34 Slot
35 Outer metal ring mounting bolt
40 Radial corrugated leaf spring 40 (radial biasing means)
50 Outer turbine axial corrugated spring
60 Inner Shroud
61 Inside Shroud Body
62 Outer surface
63 Inner groove
70 Inner metal ring
71 Inside metal ring body
72 Inner claw
73 Inside cooling gas hole
74 Inside protrusion
80 Inner turbine axial corrugated leaf spring
91 Stationary wing
92 Outer metal ring
93 Outside thin plate
94 mounting bolt
95 Outer spring
96 Outer mounting bolt
97 Inner metal ring
98 inner spring
99 Inside mounting bolt

Claims (9)

A turbine vane structure having a gas passage having an annular cross section around a turbine axis,
An outer shroud whose inner peripheral surface forms the outer periphery of the gas passage;
An inner shroud whose outer peripheral surface forms the inner periphery of the gas passage;
A stationary blade that is a long member having a cross section in which a longitudinal axis extends in the radial direction and is enveloped between the outer shroud and the inner shroud and has an envelope shape,
With
One end of the vane fits or is secured to one of the outer shroud or the inner shroud,
A turbine vane structure, wherein the other end of the vane abuts on the other of the outer shroud or the inner shroud and is slidable at least in the turbine axial direction. 2. The turbine vane structure according to claim 1, further comprising a radial biasing unit that biases the outer shroud and the inner shroud in a direction toward each other. 3. An outer metal ring fixed to a turbine casing, the outer shroud having a pair of front and rear outer grooves provided along a turbine axis;
3. The turbine vane structure according to claim 1, wherein the outer metal ring includes a pair of front and rear outer claw portions that gently engage with the outer groove portions. 4. 4. The turbine vane structure according to claim 3, wherein the outer metal ring has a plurality of protrusions that contact an outer peripheral portion of the outer shroud. 5. The outer metal ring has an outer cooling gas hole,
Cooling gas enters the gap between the outer metal ring and the outer shroud from the outer cooling gas hole, and blows out to the gas passage from the gap where the outer groove and the outer claw are engaged. 5. The turbine vane structure according to claim 3, wherein: With an inner metal ring fixed to the bearing housing of the turbine,
The inner shroud has a pair of front and rear inner grooves provided around the turbine axis,
6. The turbine vane structure according to claim 1, wherein the inner metal ring includes a pair of front and rear inner claws that gently engage with the inner groove. 7. 7. The turbine vane structure according to claim 6, wherein the inner metal ring has a plurality of protrusions abutting on an inner peripheral portion of the inner shroud. 8. The inner metal ring has an inner cooling gas hole,
Cooling gas enters the gap between the inner metal ring and the inner shroud from the inner cooling gas hole, and blows out to the gas passage from the gap where the inner groove and the inner claw are engaged. 8. The turbine vane structure according to claim 6, wherein: 9. The turbine vane according to claim 2, wherein the radial urging means is a corrugated spring provided on an outer peripheral portion of the outer shroud or an inner peripheral portion of the inner shroud. 10. Construction.

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