JP2020133567A - Member for rotary machine - Google Patents

Abstract

To provide a member for a rotary machine capable of further improving efficiency of the rotary machine.SOLUTION: A member for a rotary machine has an annular member body A that extends in a circumferential direction around an axial line Am. The annular member body A has a plurality of base plates made of a first material and laminated at intervals in the circumferential direction, and a plurality of beams made of a second material and connecting adjacent base plates to each other. The linear expansion coefficient of the first material has a non-thermal expansion structure larger than the linear expansion coefficient of the second material.SELECTED DRAWING: Figure 2

Description

The present invention relates to members for rotary machines.

The gas turbine includes a compressor, a combustor, and a turbine. The compressor compresses the outside air to produce high pressure air. The combustor produces high-temperature and high-pressure combustion gas by mixing and burning the high-pressure air and fuel. The turbine is rotationally driven by this combustion gas. Here, high-temperature fluid is normally circulated on the outlet side (rear stage side) of the compressor and the inlet side of the turbine. Therefore, the member forming the region often undergoes deformation (thermal deformation) due to heat input.

By the way, for example, a clearance of about several mm is generally formed between the tip of the rotor blade of the turbine and the inner peripheral surface of the vehicle interior. This clearance is formed to ensure smooth rotation of the rotor. However, if the above-mentioned thermal deformation occurs in each member, it may not be possible to maintain this clearance normally. If the clearance becomes excessively small or uneven in the circumferential direction of the rotor, the rotor blades may come into contact with the passenger compartment and the turbine may not operate normally.

Therefore, Patent Document 1 below proposes that a high-temperature member of a gas turbine is constructed of a composite material. This composite material is formed by alternately laminating a first material having a negative coefficient of thermal expansion or a negative Poisson's ratio and a second material having a positive coefficient of thermal expansion or a positive Poisson's ratio. Has been done. Therefore, when exposed to heat, the first material shrinks and the second material expands in this composite. As a result, it is said that thermal expansion (thermal deformation) does not occur in the composite material as a whole.

Japanese Unexamined Patent Publication No. 2008-232149

However, in the composite material described in Patent Document 1, since the first material and the second material are simply laminated, it is difficult to arbitrarily define the direction of shrinkage / expansion thereof. On the other hand, in order to use it as a high-temperature member of a gas turbine, it is desirable that not only the amount of thermal deformation but also the direction in which thermal deformation occurs is strictly defined in order to maintain the above-mentioned clearance.

The present invention has been made to solve the above problems, and an object of the present invention is to provide a member for a rotating machine capable of further improving the efficiency of the rotating machine.

The member for a rotating machine according to one aspect of the present invention has an annular member main body extending in the circumferential direction about an axis, and the annular member main body is made of a first material and a plurality of members are laminated in the circumferential direction at intervals. It has a non-thermal expansion structure having a base plate and a plurality of beams connecting adjacent base plates made of a second material, and the coefficient of linear expansion of the first material is the line of the second material. Greater than the coefficient of expansion.

According to the above configuration, the annular member body has a non-thermal expansion structure. This non-thermal expansion structure is formed by a base plate laminated at intervals and a non-thermal expansion member having a plurality of beams connecting the base plates. The first material forming the base plate has a larger coefficient of linear expansion than the second material forming the beam. Therefore, when heat is applied to the annular member body, the base plate undergoes thermal deformation in the direction of its own surface, while the thermal deformation generated in the beam becomes small. As a result, the amount of thermal deformation of the base plate in the laminating direction becomes zero or a negative value, or becomes a very small positive value as compared with the case where the first material and the second material are used alone. In the above configuration, the stacking direction of these base plates is the circumferential direction of the annular member main body. Therefore, the thermal deformation of the annular member body in this direction is zero or a negative value. By applying such a member for a rotating machine to a portion where thermal deformation in the circumferential direction is not desired to occur, for example, an excessive change in clearance due to thermal deformation can be avoided.

The members for a rotating machine include a compressor rotor that can rotate around an axis, and a compressor chassis that has a tubular shape that covers the compressor rotor from the outer peripheral side and is provided with a plurality of compressor stationary blades on the inner peripheral surface. The annular member main body may be a stationary blade holding ring that further supports the plurality of compressor stationary blades on the inner peripheral side of the compressor casing.

According to the above configuration, the annular member main body as the stationary blade holding ring has a non-thermal expansion structure, and in the non-thermal expansion structure, the stacking direction of the base plate is the circumferential direction of the annular member main body. As a result, the thermal deformation in the circumferential direction of the stationary blade holding ring becomes zero or a negative value. Therefore, the inner diameter dimension of the stationary blade holding ring does not change or only changes in the direction of slightly increasing. As a result, it is possible to reduce the possibility that the clearance between the tip of the compressor vane and the vane holding ring becomes excessively large.

The members for rotating machinery have a turbine rotor that can rotate around an axis, a plurality of turbine blades provided on the outer peripheral surface of the turbine rotor, and a tubular shape that covers the turbine rotor from the outer peripheral side and an inner peripheral surface. A turbine cabin in which a plurality of turbine blades are provided, and an annular split ring centered on an axis, which is arranged with a radial outer end of the turbine blade and a clearance in the radial direction. The annular member main body may be a turbine blade ring that supports the divided ring on the inner peripheral side of the turbine casing.

According to the above configuration, the annular member main body as the turbine blade ring has a non-thermal expansion structure, and in the non-thermal expansion structure, the stacking direction of the base plate is the circumferential direction of the annular member main body. As a result, the thermal deformation in the circumferential direction of the turbine blade ring becomes zero or a negative value. Therefore, the inner diameter dimension of the turbine blade ring does not change or only changes in the direction of slightly increasing. As a result, it is possible to reduce the possibility that the clearance between the split ring supported on the inner peripheral side by the turbine blade ring and the radial outer end of the turbine blade becomes excessively large.

The members for a rotating machine include a turbine rotor that can rotate around an axis, a turbine casing that has a tubular shape that covers the turbine rotor from the outer peripheral side, and a plurality of turbine vanes provided on the inner peripheral surface. The annular member body further comprises a seal ring for sealing fluid leakage between the radially inner end of the turbine vane and the turbine rotor, and the annular member body holds the seal ring in the radial direction of the turbine vane. It may be a seal ring holding ring supported by the inner end.

According to the above configuration, the annular member main body as the seal ring holding ring has a non-thermal expansion structure, and in the non-thermal expansion structure, the stacking direction of the base plate is the circumferential direction of the annular member main body. As a result, the thermal deformation of the seal ring holding ring in the circumferential direction becomes zero or a negative value. Therefore, the inner diameter dimension of the seal ring holding ring does not change or only changes in the direction of slightly increasing. As a result, it is possible to reduce the possibility that the clearance between the seal ring supported on the inner peripheral side by the seal ring holding ring and the turbine rotor becomes excessively large.

The rotary machine member may further include a membrane member that covers at least a part of the surface of the non-thermal expansion structure of the annular member body.

In the non-thermal expansion structure constituting the annular member main body, a space is formed between the base plates adjacent to each other and between the beams. If a fluid flows into this space, it may lead to inadvertent pressure loss or flow obstruction. However, in the above configuration, at least a part of the surface of the non-thermal expansion structure is covered with a film member. Therefore, the inflow of fluid into the above space can be suppressed.

The rotary machine member has an annular member main body extending in the circumferential direction about the axis, and the annular member main body is made of a first material and a plurality of base plates are laminated in the radial direction of the axis at intervals. It has a non-thermal expansion structure having a plurality of beams made of a second material and connecting adjacent base plates to each other, and the linear expansion coefficient of the first material is larger than the linear expansion coefficient of the second material. ..

According to the above configuration, the annular member body has a non-thermal expansion structure. This non-thermal expansion structure is formed by a base plate laminated at intervals and a non-thermal expansion member having a plurality of beams connecting the base plates. The first material forming the base plate has a larger coefficient of linear expansion than the second material forming the beam. Therefore, when heat is applied to the annular member body, the base plate undergoes thermal deformation in the direction of its own surface, while the thermal deformation generated in the beam becomes small. As a result, the amount of thermal deformation of the base plate in the laminating direction becomes zero or a negative value, or becomes a very small positive value as compared with the case where the first material and the second material are used alone. In the above configuration, the stacking direction of these base plates is the radial direction of the annular member main body. Therefore, the thermal deformation of the annular member body in this direction is zero or a negative value. By applying such a member for a rotating machine to a portion where thermal deformation in the radial direction is not desired to occur, for example, an excessive change in clearance due to thermal deformation can be avoided.

The member for a rotating machine according to one aspect of the present invention has an annular member main body extending in the circumferential direction about an axis, and the annular member main body is made of a first material and a plurality of members are spaced apart in the radial direction of the axis. It has a non-thermal expansion structure having a base plate laminated in a row and a plurality of beams made of a second material and connecting the base plates adjacent to each other, and the linear expansion coefficient of the first material is the first. The temperature is larger than the coefficient of linear expansion of the second material, and the second temperature higher than the first temperature is smaller than the coefficient of linear expansion of the second material.

According to the above configuration, below the first temperature, the coefficient of linear expansion of the first material constituting the base plate is larger than the coefficient of linear expansion of the second material. Therefore, below the first temperature, the non-thermal expansion member exhibits zero or a negative coefficient of linear expansion. On the other hand, at the second temperature, which is larger than the first temperature, the coefficient of linear expansion of the first material changes to be smaller than the coefficient of linear expansion of the second material. Therefore, at the second temperature, the non-thermal expansion coefficient shows a positive linear expansion coefficient. As a member for a rotary machine, it is suitable for a member that requires a change in the coefficient of linear expansion as described above from the start of operation to a steady state, for example, in order to keep the clearance between the member and another member constant. Can be applied to.

The members for rotary machinery have a turbine rotor that can rotate around an axis, a plurality of turbine moving blades provided on the outer peripheral surface of the turbine rotor, and a tubular shape that covers the turbine rotor from the outer peripheral side and an inner peripheral surface. A turbine cabin provided with a plurality of turbine stationary blades, and an annular split ring centered on the axis line, which is arranged with a radial outer end of the turbine moving blade and a clearance in the radial direction. The turbine wing ring that supports the split ring on the inner peripheral side of the turbine casing and the annular member main body may be a heat shield ring provided between the turbine wing ring and the split ring. ..

According to the above configuration, when the temperature is low (below the first temperature), the annular member body as the heat shield ring exhibits a negative coefficient of linear expansion and therefore contracts as a whole. On the other hand, in the operating range where the temperature is low (that is, immediately after the start of operation), the turbine blades thermally expand. Therefore, if no measures are taken, the clearance between the split ring and the turbine blades will be small. However, according to the above configuration, the clearance between the split ring and the radial outer end of the turbine blade changes in a direction of increasing due to the first contraction of the heat shield ring having the non-thermal expansion structure. Further, when the steady state is reached, the coefficient of linear expansion of the heat shield ring becomes positive. As a result, the heat shield ring expands and the clearance changes in the direction of decreasing. Therefore, it is possible to maintain the size of the clearance at a constant value from immediately after the start of operation to the steady state. As a result, the efficiency of the gas turbine can be further improved.

The rotary machine member may further have a film-like film member that covers at least a part of the surface of the non-thermal expansion structure of the annular member body.

In the non-thermal expansion structure constituting the annular member main body, a space is formed between the base plates adjacent to each other and between the beams. If a fluid flows into this space, it may lead to inadvertent pressure loss or flow obstruction. However, in the above configuration, at least a part of the surface of the non-thermal expansion structure is covered with a film member. Therefore, the inflow of fluid into the above space can be suppressed.

According to the present invention, it is possible to provide a member for a rotating machine capable of further improving the efficiency of the rotating machine.

It is a schematic diagram which shows the structure of the gas turbine which concerns on 1st Embodiment of this invention. It is an enlarged sectional view of the main part of the gas turbine which concerns on 1st Embodiment of this invention. It is a perspective view which shows the structure of the non-thermal expansion member which concerns on 1st Embodiment of this invention. It is explanatory drawing which shows the behavior of the non-thermal expansion member. It is an enlarged sectional view of the main part of the gas turbine which concerns on 2nd Embodiment of this invention. It is an enlarged sectional view of the main part of the gas turbine which concerns on 3rd Embodiment of this invention. It is a graph which shows the relationship between the linear expansion coefficient of the 1st material which comprises the non-thermal expansion member which concerns on 3rd Embodiment of this invention, and the 2nd material, and temperature. It is a graph which shows the relationship between the linear expansion coefficient and the temperature of the non-thermal expansion member which concerns on 3rd Embodiment of this invention. It is an enlarged sectional view of the main part of the gas turbine which concerns on 4th Embodiment of this invention. It is an enlarged sectional view of the main part of the gas turbine which concerns on 5th Embodiment of this invention. It is an enlarged sectional view of the main part which shows the modification of the gas turbine which concerns on 5th Embodiment of this invention.

[First Embodiment]
The first embodiment of the present invention will be described with reference to FIGS. 1 to 4. The gas turbine 100 includes a compressor 1, a combustor 3, and a turbine 2.

The compressor 1 produces high pressure air. The compressor 1 includes a compressor rotor 11 and a compressor casing 12 (compressor casing) as members for a rotating machine. The compressor casing 12 covers the compressor rotor 11 from the outer peripheral side and extends along the axis Am.

A plurality of compressor moving blade stages 13 arranged at intervals in the axis direction Am are provided on the outer peripheral surface of the compressor rotor 11. Each of these compression motor blade stages 13 includes a plurality of compression mobile blades 14. The compressor vanes 14 of each compressor vane stage 13 are arranged on the outer peripheral surface of the compressor rotor 11 at intervals in the circumferential direction of the axis Am.

On the inner peripheral surface of the compressor casing 12, a plurality of compressor stationary blade stages 15 arranged at intervals in the axis Am direction are provided. These compressor stationary blade stages 15 are arranged alternately with the compressor moving blade stage 13 in the direction of the axis Am. Each of these compressor stationary blade stages 15 includes a plurality of compressor stationary blades 16. The compressor stationary blades 16 of each compressor stationary blade stage 15 are arranged on the inner peripheral surface of the compressor casing 12 at intervals in the circumferential direction of the axis Am.

The combustor 3 produces combustion gas by mixing fuel with the high-pressure air generated by the compressor 1 and burning the fuel. The combustor 3 is provided between the compressor casing 12 and the turbine casing 22 of the turbine 2. The combustion gas generated by the combustor 3 is supplied to the turbine 2.

The turbine 2 is driven by the combustion gas generated by the combustor 3. The turbine 2 has a turbine rotor 21 and a turbine casing 22 (turbine casing) as members for rotary machinery. The turbine rotor 21 extends along the axis Am. A plurality of turbine blade stages 23 arranged at intervals in the axis Am direction are provided on the outer peripheral surface of the turbine rotor 21. Each of these turbine blade stages 23 includes a plurality of turbine blades 24. The turbine blades 24 of each turbine blade stage 23 are arranged on the outer peripheral surface of the turbine rotor 21 at intervals in the circumferential direction of the axis Am.

The turbine casing 22 covers the turbine rotor 21 from the outer peripheral side. A plurality of turbine stationary blade stages 25 arranged at intervals in the axis Am direction are provided on the inner peripheral surface of the turbine casing 22. The turbine blade stages 25 are arranged alternately with the turbine blade stages 23 in the direction of the axis Am. Each of these turbine stationary blade stages 25 includes a plurality of turbine stationary blades 26. The turbine stationary blades 26 of each turbine stationary blade stage 25 are arranged on the inner peripheral surface of the turbine casing 22 at intervals in the circumferential direction of the axis Am.

The compressor rotor 11 and the turbine rotor 21 are integrally connected in the direction of the axis Am. The gas turbine rotor 91 (turbine rotor) is composed of the compressor rotor 11 and the turbine rotor 21. Similarly, the compressor casing 12 and the turbine casing 22 are integrally connected along the axis Am. The gas turbine casing 92 (vehicle compartment) is composed of the compressor casing 12 and the turbine casing 22. The gas turbine rotor 91 is integrally rotatable around the axis Am inside the gas turbine casing 92.

In operating the gas turbine 100, first, the compressor rotor 11 (gas turbine rotor 91) is rotationally driven by an external drive source. As the compressor rotor 11 rotates, the external air is sequentially compressed to generate high-pressure air. This high-pressure air is supplied into the combustor 3 through the compressor casing 12. In the combustor 3, fuel is mixed with the high-pressure air and burned to generate high-temperature and high-pressure combustion gas. The combustion gas is supplied into the turbine 2 through the turbine casing 22. In the turbine 2, rotational driving force is applied to the turbine rotor 21 (gas turbine rotor 91) by sequentially colliding the combustion gas with the turbine blade stage 23 and the turbine stationary blade stage 25. This rotational energy is used, for example, to drive a generator G or the like connected to the shaft end. The combustion gas that drives the turbine 2 is discharged to the outside.

Next, the internal configuration of the compressor 1 will be described with reference to FIG. As shown in the figure, in the compressor 1, the above-mentioned compressor stationary blade 16 is held inside the compressor casing 12 by a stationary blade holding ring 30 (annular member main body A). Specifically, the stationary blade holding ring 30 is fixed to the tip (diameter inner end) of the protrusion S1 protruding inward in the radial direction from the inner peripheral surface of the compressor casing 12 with respect to the axis Am. There is. The stationary blade holding ring 30 has a tubular shape centered on the axis Am. A plurality of compressors are static on the inner peripheral surface 31S of the stationary blade holding ring 30 including the end portion on one side in the axis Am direction (that is, the portion on one side in the axis Am direction from the above-mentioned protruding portion S1). The wings 16 are arranged at intervals in the direction of the axis Am. One compressor moving blade 14 is inserted between the pair of compressor stationary blades 16. A clearance C1 that extends in the radial direction is formed between the tip end portion (the end portion on the outer side in the radial direction) of the compressor blade 14 and the inner peripheral surface 31S.

The inner peripheral surface 32S of the stationary blade holding ring 30 including the end portion on the other side in the axis Am direction (that is, the portion on the other side in the axis Am direction from the protrusion S1) is from one side in the axis Am direction. It extends from the inside to the outside in the radial direction toward the other side. Further, the inner peripheral surface 32S faces the outer peripheral surface 5S of the diffuser 5 from the outside in the radial direction. The diffuser 5 is provided to guide the high-pressure air discharged from the compressor 1 and restore the static pressure.

The stationary blade holding ring 30 is formed by a non-thermal expansion member M having a non-thermal expansion structure. Non-thermal expansion structures have a coefficient of linear expansion of zero, a negative value, or a very small positive value. As shown in FIG. 3, the non-thermal expansion member M is formed in a plate shape, and a plurality of base plates 81 arranged in parallel with each other at intervals in the thickness direction, and these base plates 81 are placed on each other. It has a three-dimensional truss structure 82 to be connected (has a non-thermal expansion structure). Both the base plate 81 and the three-dimensional truss structure 82 are made of a metal material. The coefficient of linear expansion of the first material forming the base plate 81 is relatively large with respect to the coefficient of linear expansion of the second material forming the three-dimensional truss structure 82. The plurality of base plates 81 face each other at equal intervals over the entire extending area.

The three-dimensional truss structure 82 has a plurality of beams 83 extending in directions intersecting each other. Each beam 83 has a rod shape. In this three-dimensional truss structure 82, the four beams 83 are one of a plurality of support points arranged in a grid pattern on the surface of the base plate 81 on one side of the pair of base plates 81 facing each other (first). The support points P1) and the four support points (second support points P2) arranged in a grid pattern on the surface of the base plate 81 on the other side are connected to each other.

The base plate 81 has a support portion S that forms a first support point P1 by connecting a plurality of (four) beams 83, and a plurality of support portions that are adjacent to each other in the spreading direction (plane direction) of the base plate 81. It has a connecting portion C for connecting S. As a result, the base plate 81 is formed with a plurality of (four) quadrangular holes (base plate hole portions H) having a plurality of (four) first support points P1 as vertices. That is, the base plate 81 has a grid pattern that connects the first support points P1 to each other.

When viewed from the direction orthogonal to the base plate 81, the first support point P1 and the second support point P2 are arranged so that their positions do not overlap each other, and are arranged in a grid pattern at equal intervals from each other. There is. That is, the four beams 83 form a quadrangular pyramid having one first support point P1 as an apex and a quadrangle formed on the base plate 81 by the four second support points P2 as a bottom surface. .. The plurality of beams 83 have the same length as each other.

The three-dimensional truss structure 82 as described above is arranged so as to be mirror image symmetric in the stacking direction with the base plate 81 interposed therebetween. In other words, the other first support point P1 is located on the opposite side of one first support point P1 on one side surface of the base plate 81 (on the other side surface of the base plate 81). In the example of FIG. 3, the unit structure composed of the base plate 81 and the three-dimensional truss structure 82 is laminated over four layers.

Next, the behavior of the non-thermal expansion member M will be described with reference to FIG. In FIG. 4, only a pair of base plates 81 and a one-layer three-dimensional truss structure 82 provided between the base plates 81 are typically shown. When heat is applied to the non-thermal expansion member M, the base plate 81 and the three-dimensional truss structure 82 behave as follows. First, the base plate 81 expands in the direction of its extending surface (expands in the Da direction in FIG. 4: base plate 1a). Therefore, the distance between the above-mentioned first support points P1 is widened (first support point P1a). Here, since the coefficient of linear expansion of the beam 83 is smaller than the coefficient of linear expansion of the base plate 81, the amount of thermal expansion of the beam 83 is smaller than the amount of thermal expansion of the base plate 81. As a result, the distance between the first support points P1 described above is widened, and the pair of beams 83 are pulled in the expanding direction of the base plate 81 (beam 83a). As a result, a force is applied to the base plate 81 on one side to displace the base plate 81 on the other side in the approaching direction. Due to this force, the base plate 81 on the other side is displaced in the Db direction in FIG. In this way, while the base plate 81 expands in the spreading plane direction, the thermal deformation becomes zero (or a negative value) in the thickness direction (stacking direction) orthogonal to the plane direction, or the first material and the first material The positive value is very small compared to the case where each of the two materials is used alone. In the example of FIG. 4, the behavior of the base plate 1 is exaggerated for the sake of explanation. That is, in reality, the base plates 1 do not displace in the direction of approaching each other, and the thermal deformation in the stacking direction becomes zero (or an extremely small value).

On the other hand, when heat is applied to a solid plate made of a uniform material, which is different from the non-thermal expansion member M as described above, thermal expansion occurs in both the surface direction and the thickness direction. It ends up. That is, the non-thermal expansion member M can realize characteristics that have not been obtained in the past.

In the stationary blade holding ring 30 according to the present embodiment, the stacking direction of the base plate 81 is the circumferential direction with respect to the axis Am. Therefore, the dimensions of the stationary blade holding ring 30 in the circumferential direction do not change or decrease. Therefore, the inner diameter dimension of the annular stationary blade holding ring 30 does not change or slightly increases. As a result, it is possible to reduce the possibility that the clearance C1 between the tip end portion of the compression motor blade 14 and the inner peripheral surface 31S of the stationary blade holding ring 30 is significantly changed.

As described above, according to the above configuration, the annular member main body A has a non-thermal expansion structure. This non-thermal expansion structure is formed by a base plate 81 laminated at intervals and a non-thermal expansion member M having a plurality of beams 83 connecting the base plates 81 to each other. The first material forming the base plate 81 has a larger coefficient of linear expansion than the second material forming the beam 83. Therefore, when heat is applied to the annular member main body A, the base plate 81 undergoes thermal deformation in its own surface direction, while the thermal deformation generated in the beam 83 becomes small. As a result, the amount of thermal deformation of the base plate 81 in the stacking direction becomes zero or a negative value. In the above configuration, the stacking direction of these base plates 81 is the circumferential direction of the annular member main body A. Therefore, the thermal deformation of the annular member body A in this direction is zero or a negative value. By applying such a member for a rotating machine to a portion where thermal deformation in the circumferential direction is not desired to occur, for example, an excessive change in clearance due to thermal deformation can be avoided.

Further, according to the above configuration, the annular member main body A as the stationary blade holding ring 30 has a non-thermal expansion structure, and in the non-thermal expansion structure, the stacking direction of the base plate 81 is the circumferential direction of the annular member main body A. Has been done. As a result, the thermal deformation of the stationary blade holding ring 30 in the circumferential direction becomes zero or a negative value. Therefore, the inner diameter dimension of the stationary blade holding ring 30 does not change or changes only slightly. As a result, it is possible to reduce the possibility that the clearance C1 between the tip of the compressor vane 14 and the vane holding ring 30 becomes excessively large. Thereby, the efficiency of the gas turbine 100 can be improved.

The first embodiment of the present invention has been described above. It should be noted that various changes and modifications can be made to the above configuration as long as the gist of the present invention is not deviated.

[Second Embodiment]
Next, the second embodiment of the present invention will be described with reference to FIG. The same components as those in the first embodiment are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, an example in which the above-mentioned non-thermal expansion member M is applied to the turbine blade ring 50 in the turbine 2 as the annular member main body B will be described. As shown in FIG. 5, inside the turbine casing 22 (turbine casing), a protruding portion S2 protruding inward in the radial direction from the inner peripheral surface 22S of the turbine casing 22 and a radial inside of the protruding portion S2. A cylindrical turbine blade ring 50 attached to the end of the turbine blade ring 50 and a split ring 70 supported via a heat shield ring 60 on the inner peripheral side of the turbine blade ring 50 are provided. The dividing ring 70 has an annular shape centered on the axis Am. The inner peripheral surface 70S of the dividing ring 70 faces the tip end portion (diameter outer end portion) of the turbine blade 24 with a clearance C2.

The turbine blade ring 50 is formed by the above-mentioned non-thermal expansion member M. The stacking direction of the base plate 81 in the non-thermal expansion member M is the circumferential direction with respect to the axis Am.

According to the above configuration, the annular member main body B as the turbine blade ring 50 has a non-thermal expansion structure, and in the non-thermal expansion structure, the stacking direction of the base plate 81 is the circumferential direction of the annular member main body B. .. As a result, the thermal deformation of the turbine blade ring 50 in the circumferential direction becomes zero or a negative value, or becomes a very small positive value as compared with the case where the first material and the second material are used alone. Therefore, the inner diameter dimension of the turbine blade ring 50 does not change, or only changes in the direction of slightly increasing. As a result, the clearance C2 between the inner peripheral surface 70S of the split ring 70 supported on the inner peripheral side by the turbine blade ring 50 and the radial outer end of the turbine blade 24 may become excessively large. Can be reduced.

The second embodiment of the present invention has been described above. It should be noted that various changes and modifications can be made to the above configuration as long as the gist of the present invention is not deviated.

[Third Embodiment]
Next, the third embodiment of the present invention will be described with reference to FIG. The same components as those of the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, an example in which the non-thermal expansion member M'is applied to the heat shield ring 60 in the turbine 2 as the annular member main body C will be described. As shown in FIG. 6, the heat shield ring 60 is provided to support the split ring 70 on the inner peripheral side of the turbine blade ring 50. Although not shown in detail, the heat shield ring 60 has a plurality of heat shield ring pieces arranged in the circumferential direction of the axis Am. The heat shield ring 60 has an annular shape centered on the axis Am as a whole.

In the non-thermal expansion member M'forming the heat shield ring 60, the stacking direction of the base plate 81 is set to be the radial direction with respect to the axis Am. Further, as shown by the chain line graph in FIG. 7, the coefficient of linear expansion of the first material forming the base plate 81 is the temperature of the second material forming the beam 83 at a temperature equal to or lower than the threshold value Tc (first temperature). It is larger than the coefficient of linear expansion (solid line graph). On the other hand, at a temperature higher than the threshold value Tc (second temperature), the coefficient of linear expansion of the first material becomes smaller than the coefficient of linear expansion of the second material. A 5Cr-1Mo-based alloy can be preferably used as the first material exhibiting such characteristics, and a 5Ni-1 / 4Mo-based alloy can be preferably used as the second material. As another combination, it is also possible to use a 12Cr (or 13Cr) alloy as the first material and a 9Cr-1Mo alloy as the second material. As yet another example, as the first material and the second material, stainless steel (SUS304, SUS310, SUS316, SUS410), Ti6Al4V, Ni-based alloy (Inconel 600, 718), high chrome steel (9Cr, 12Cr), A material selected from 2.25Cr-1Mo material and the like is appropriately used. More specifically, it is conceivable to use SUS304 as the first material and SUS410 as the second material having a coefficient of linear expansion smaller than that of SUS304. It is also possible to use SUS304 as the first material and Ti6Al4V as the second material. In addition, aluminum alloy, copper, and carbon steel can be used as the first material or the second material.

The non-thermal expansion member M'forming the heat shield ring 60 by being formed of the first material and the second material as described above shows a linear expansion coefficient as shown in FIG. Specifically, it shows a zero or negative coefficient of linear expansion in a temperature region below the threshold Tc, and shows a positive coefficient of linear expansion in a temperature region higher than the threshold Tc.

According to the above configuration, the annular member body C has a non-thermal expansion structure. This non-thermal expansion structure is formed by a base plate 81 laminated at intervals and a non-thermal expansion member M'having a plurality of beams 83 connecting the base plates 81 to each other. The first material forming the base plate 81 has a larger coefficient of linear expansion than the second material forming the beam 83. Therefore, when heat is applied to the annular member main body C, the base plate 81 undergoes thermal deformation in its own surface direction, while the thermal deformation generated in the beam 83 becomes small. As a result, the amount of thermal deformation of the base plate 81 in the stacking direction becomes zero or a negative value. In the above configuration, the stacking direction of these base plates 81 is the radial direction of the annular member main body C. Therefore, the thermal deformation of the annular member body C in this direction is zero or a negative value. By applying such a member for a rotating machine to a portion where thermal deformation in the radial direction is not desired to occur, for example, an excessive change in clearance due to thermal deformation can be avoided.

Further, according to the above configuration, the coefficient of linear expansion of the first material constituting the base plate 81 is larger than the coefficient of linear expansion of the second material below the predetermined first temperature. Therefore, below the first temperature, the non-thermal expansion member exhibits zero or a negative coefficient of linear expansion. On the other hand, at the second temperature, which is larger than the first temperature, the coefficient of linear expansion of the first material changes to be smaller than the coefficient of linear expansion of the second material. Therefore, at the second temperature, the non-thermal expansion member exhibits a positive coefficient of linear expansion. As a member for a rotary machine, it is suitable for a member that requires a change in the coefficient of linear expansion as described above from the start of operation to a steady state, for example, in order to keep the clearance between the member and another member constant. Can be applied to.

Therefore, in the above embodiment, the non-thermal expansion member M'is applied to the heat shield ring 60. When the temperature is low (below the first temperature), the annular member body C as the heat shield ring 60 exhibits a negative coefficient of linear expansion and therefore contracts as a whole. On the other hand, in the operating region where the temperature is low (that is, immediately after the start of operation), the turbine blade 24 gradually expands from the cold state. Therefore, if no measures are taken, the clearance C2 between the split ring 70 and the turbine blade 24 will be small. However, according to the above configuration, the clearance C2 between the split ring 70 and the radial outer end of the turbine blade 24 increases due to the first contraction of the heat shield ring 60 having the non-thermal expansion structure. Changes to. Further, when the steady state is reached, the coefficient of linear expansion of the heat shield ring 60 becomes positive. As a result, the heat shield ring 60 expands, and the clearance C2 changes in the direction of becoming smaller. Therefore, it is possible to maintain the size of the clearance C2 at a constant value from immediately after the start of operation to the steady state. As a result, the efficiency of the gas turbine 100 can be further improved.

The third embodiment of the present invention has been described above. It should be noted that various changes and modifications can be made to the above configuration as long as the gist of the present invention is not deviated.

[Fourth Embodiment]
Subsequently, the fourth embodiment of the present invention will be described with reference to FIG. The same components as those of the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, an example in which the above-mentioned non-thermal expansion member M is applied to the seal ring holding ring 90 in the turbine 2 as the annular member main body D will be described. As shown in FIG. 9, the tip portion of the turbine stationary blade 26 is located between the pair of turbine blades 24 adjacent to each other in the turbine 2.

Specifically, each turbine rotor blade 24 has a turbine rotor blade main body 24A and a platform 24B that supports the turbine rotor blade main body 24A on the outer peripheral surface of the turbine rotor 21. The platform 24B has a platform main body 241 extending in the radial direction with respect to the axis Am, and an overhanging portion 242 extending from the radial inside of the platform main body 241 to both sides in the axial direction Am. The overhanging portion 242 of the turbine rotor blade 24 on one side in the axis Am direction faces the overhanging portion 242 in the other turbine rotor blade 24 adjacent to the other side in the axis Am direction.

The turbine stationary blade 26 includes a turbine stationary blade main body 26A, an inner shroud 26B provided at the radially inner end of the turbine stationary blade main body 26A, and a seal ring holding ring provided further radially inside the inner shroud 26B. It has 90 and. The inner shroud 26B has a plate-shaped shroud main body 261 connected to the turbine stationary blade main body 26A, and a connecting portion 262 protruding inward in the radial direction from the shroud main body 261. The seal ring holding ring 90 forms an annular shape centered on the axis Am, and an insertion groove 90R into which the connection portion 262 is inserted is formed on the end face facing outward in the radial direction. A plurality (two) of seal rings Sr are attached to the radial inner end faces of the seal ring holding ring 90. The seal ring Sr located on one side in the direction of the axis Am faces the overhanging portion 242 of the turbine blade 24 on one side of the pair of turbine blades 24 adjacent to each other with a clearance C3. The seal ring Sr located on the other side in the Am direction of the axis line faces the overhanging portion 242 of the turbine blade 24 on the other side with a clearance C3. The seal ring Sr is provided to seal the fluid leakage through the clearance C3.

The seal ring holding ring 90 is formed by the above-mentioned non-thermal expansion member M. The stacking direction of the base plate 81 in the non-thermal expansion member M is the circumferential direction with respect to the axis Am.

According to the above configuration, the annular member main body D as the seal ring holding ring 90 has a non-thermal expansion structure, and in the non-thermal expansion structure, the stacking direction of the base plate 81 is the circumferential direction of the annular member main body D. There is. As a result, the thermal deformation of the seal ring holding ring 90 in the circumferential direction becomes zero or a negative value. Therefore, the inner diameter dimension of the seal ring holding ring 90 does not change, or only changes in the direction of slightly increasing. As a result, it is possible to reduce the possibility that the clearance C3 between the seal ring Sr supported on the inner peripheral side by the seal ring holding ring 90 and the turbine rotor 21 (turbine rotor blade 24) becomes excessively large. ..

The fourth embodiment of the present invention has been described above. It should be noted that various changes and modifications can be made to the above configuration as long as the gist of the present invention is not deviated.

[Fifth Embodiment]
Subsequently, the fifth embodiment of the present invention will be described with reference to FIG. The same components as those of the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. As shown in FIG. 10, in the present embodiment, a film-like film member W covering at least a part of the stationary blade holding ring 30 is provided outside the stationary blade holding ring 30 described in the first embodiment. There is. In the example of FIG. 10, the entire outer surface of the stationary blade holding ring 30 is covered with the film member W.

Here, in the non-thermal expansion structure M, a space is formed between the base plates 81 adjacent to each other and between the beams 83. If a fluid flows into this space, it may lead to inadvertent pressure loss or flow obstruction. However, in the above configuration, at least a part of the surface of the stationary blade holding ring 30 formed by the non-thermal expansion structure M is covered with the film member W. Therefore, the inflow of fluid into the above space can be suppressed. As a result, the above-mentioned disturbance due to pressure loss and flow can be avoided, and the efficiency of the gas turbine 100 can be further improved.

The fifth embodiment of the present invention has been described above. It should be noted that various changes and modifications can be made to the above configuration as long as the gist of the present invention is not deviated. For example, as shown in FIG. 11, it is possible to provide the partition member W2 made of the same material as the film member W not only on the outer surface of the stationary blade holding ring 30 but also on the inside. The partition member W2 divides the inside of the stationary blade holding ring 30 into a plurality of sections. According to this configuration, the rigidity of the stationary blade holding ring 30 can be further increased.

Further, the film member W described in the present embodiment can be applied to the annular member bodies B, C, and D described in the first to fourth embodiments described above.

1 ... Compressor 2 ... Turbine 3 ... Combustor 5 ... Diffuser 6 ... Bearing 11 ... Compressor rotor 12 ... Compressor casing 13 ... Compressor moving blade stage 14 ... Compressor moving blade 15 ... Compressor stationary blade stage 16 ... Compressor static Blade 21 ... Turbine rotor 22 ... Turbine casing 23 ... Turbine moving blade stage 24 ... Turbine moving blade 25 ... Turbine stationary blade stage 26 ... Turbine stationary blade 30 ... Static blade holding ring 50 ... Turbine blade ring 60 ... Heat shield ring 70 ... Split Ring 81 ... Base plate 82 ... Three-dimensional truss structure 83 ... Beam 90 ... Seal ring holding ring 91 ... Gas turbine rotor 92 ... Gas turbine casing 100 ... Gas turbine 241 ... Platform body 242 ... Overhang 261 ... Shroud body 262 ... Connection Part 24A ... Turbine moving blade body 24B ... Platform 26A ... Turbine stationary blade body 26B ... Inner shroud 90R ... Insert groove A, B, C, D ... Ring member Am ... Axis line C ... Connection part C1, C2, C3 ... Clearance H ... Base plate hole M, M'... Non-thermal expansion member P1 ... First support point P2 ... Second support point S ... Support part Sr ... Seal ring W ... Membrane member W2 ... Partition member

Claims (9)

It has an annular member body that extends in the circumferential direction around the axis.
The annular member body
It has a non-thermal expansion structure having a base plate made of a first material and having a plurality of laminated layers in the circumferential direction at intervals, and a plurality of beams made of a second material and connecting adjacent base plates to each other.
A member for a rotating machine in which the coefficient of linear expansion of the first material is larger than the coefficient of linear expansion of the second material. A compressor rotor that can rotate around the axis, a tubular compressor chassis that covers the compressor rotor from the outer peripheral side, and a plurality of compressor stationary blades provided on the inner peripheral surface of the compressor chassis. Have more
The member for a rotating machine according to claim 1, wherein the annular member main body is a stationary blade holding ring that supports the plurality of compressor stationary blades on the inner peripheral side of the compressor casing. A turbine rotor that can rotate around the axis, a plurality of turbine moving blades provided on the outer peripheral surface of the turbine rotor, and a plurality of turbine vanes on the inner peripheral surface while forming a tubular shape that covers the turbine rotor from the outer peripheral side. It further has a turbine casing provided, a radial outer end of the turbine blade and an annular split ring arranged radially through a clearance and centered on an axis.
The member for a rotating machine according to claim 1, wherein the annular member main body is a turbine blade ring that supports the divided ring on the inner peripheral side of the turbine casing. A turbine rotor that can rotate around the axis, a turbine casing that has a tubular shape that covers the turbine rotor from the outer peripheral side and is provided with a plurality of turbine vanes on the inner peripheral surface, and a radial inside of the turbine vanes. Further has a seal ring, which seals a fluid leak between the end of the turbine rotor and the turbine rotor.
The member for a rotating machine according to claim 1, wherein the annular member main body is a seal ring holding ring that supports the seal ring at a radial inner end of the turbine stationary blade. The member for a rotating machine according to any one of claims 1 to 4, further comprising a film member that covers at least a part of the surface of the non-thermal expansion structure of the annular member body. It has an annular member body that extends in the circumferential direction around the axis.
The annular member body
It has a non-thermal expansion structure having a base plate made of the first material and having a plurality of laminated layers in the radial direction of the axis, and a plurality of beams made of the second material and connecting adjacent base plates to each other. And
A member for a rotating machine whose linear expansion coefficient of the first material is larger than the linear expansion coefficient of the second material. It has an annular member body that extends in the circumferential direction around the axis.
The annular member body
A non-thermal expansion structure having a base plate made of a first material and having a plurality of laminated layers in the radial direction of the axis, and a plurality of beams made of a second material and connecting the base plates adjacent to each other. Have and
The coefficient of linear expansion of the first material is larger than the coefficient of linear expansion of the second material at the first temperature, and is larger than the coefficient of linear expansion of the second material at a second temperature higher than the first temperature. A small member for rotating machines. A turbine rotor that can rotate around the axis, a plurality of turbine blades provided on the outer peripheral surface of the turbine rotor, and a plurality of turbine blades that cover the turbine rotor from the outer peripheral side and have a plurality of turbine blades on the inner peripheral surface. An annular dividing ring centered on the axis and the divided ring, which are arranged radially with a clearance between the provided turbine casing and the radially outer end of the turbine blade, and the divided ring of the turbine. The turbine blade ring supported on the inner circumference side of the passenger compartment and
The member for a rotating machine according to claim 6 or 7, wherein the annular member main body is a heat shield ring provided between the turbine blade ring and the split ring. The member for a rotating machine according to any one of claims 6 to 8, further comprising a film member that covers at least a part of the surface of the non-thermal expansion structure of the annular member body.