JP4498964B2 - Turbine blade and turbine equipment using the same - Google Patents

Description

  The present invention relates to a turbine rotor blade used for a gas turbine, a steam turbine, and the like, and a turbine facility using the same.

  In turbine rotor blades used in gas turbines and steam turbines, there is a method of connecting adjacent blades in order to provide highly reliable blades. As a measure for connecting the adjacent blades, the opposed portion of the connecting cover (integral cover) extending in the blade rotation direction at the tip of the blade profile portion is inclined with respect to the turbine rotation axis direction, and this inclined opposed portion is provided. There is a type in which the integral cover of the adjacent wing is strongly connected by pressing and assembling the wing in the rotational direction (circumferential direction). In addition, in order to eliminate the rotational displacement around the blade that occurs when the blade is attached to the turbine rotation shaft, there is a type in which a rotation prevention key is provided at the lower end of the male duff tail (blade root). (For example, refer to Patent Document 1).

JP 2004-257385A.

  The above-mentioned measures for connecting adjacent blades to each other are as follows. The cover is configured so that the covers are in contact with each other and restrained.For example, a pre-twisted connection structure is used. The adjacent integral covers come into contact with each other and are restrained, and the blades are torsionally deformed. Receives rotational force. Generation of this rotational force also acts on the blade root and the disk groove that are engaged with each other, but the engagement portion between the blade root and the disk groove is inward of the radial direction of the disk groove when viewed from the turbine rotation axis direction. A force in the inner oblique direction acts on the engaging portion between the blade root portion and the disk groove.

  On the other hand, due to the fact that the engagement portion between the blade root and the disk groove is provided with a gap in consideration of normal assembly and the shape of the tapered disk groove described above, the blade root is It is pressed toward one side of the disk groove in an oblique inner direction.

  As a result, one-side contact occurs at the engaging portion between the blade root portion and the disk groove. As a result, high stress is generated in the engaging portion, and there is a risk that a problem in strength occurs because the turbine is rotated at a high speed. In addition, the contact force between adjacent integral covers may be reduced, and the original function of the pretwisted connection structure may be impaired.

  The object of the present invention has been made based on the above-mentioned matters, and even with a short blade, by preventing the rotation of the blade root, adjacent integral covers can be reliably connected, and the blade An object of the present invention is to provide a highly reliable turbine blade capable of reducing stress acting on the root portion and a turbine equipment using the turbine blade.

In order to achieve the above object, a first invention includes a blade root portion that is inserted and engaged with a plurality of disk grooves provided on the outer peripheral portion of a turbine disk in the blade rotation direction from the turbine axial direction side, and a blade profile. Integral cover integrally formed at the tip of the part, and adjacent integral covers by elastic restoring force of the blade profile part to be torsionally deformed by being pushed into the turbine disk from the turbine rotating shaft direction side A turbine rotor blade configured to contact and restrain the rotor blade, and a groove provided on the end surface on the turbine disk axial direction inlet side and outlet side through the lower part of the disk groove along the blade rotation direction, and pushed into the disk groove A radially inner peripheral surface provided to substantially coincide with a radially outer peripheral surface of the groove, and a radial direction of the blade root portion. A pressing member incorporated in the groove so that the outer peripheral surface in the radial direction abuts on the peripheral surface, and a notch portion provided on the end surface of the turbine disk and capable of inserting the pressing member into the groove from the turbine rotating shaft direction side The groove and the pressing member incorporated in the groove have a cross-sectional shape having a radially outer end surface and an inner peripheral end surface, and the pressing member has a radial height in the insertion direction in the circumferential direction. characterized by comprising a radial outer peripheral surface and the inner peripheral surface of reduced gradually to.

In addition, the second invention is integrally formed at the tip of the blade profile portion and the blade root portion that is inserted into and engaged with the disk grooves provided on the outer peripheral portion of the turbine disk in the blade rotation direction from the turbine axial direction side. The adjacent integral covers by the elastic restoring force of the blade profile portion to be torsionally deformed by being pushed into the turbine disk from the turbine rotating shaft direction side. A turbine blade configured as described above, a groove provided in the turbine disk axial direction inlet side and outlet side end face along the blade rotation direction through the lower part of the disk groove, and a tip side end face of the blade root portion to be pushed into the disk groove A radially inner circumferential surface provided so as to substantially coincide with a radially outer circumferential surface of the groove, and a radially outer circumferential surface on a radially inner circumferential surface of the blade root portion. And a pressing member in which the incorporated in the groove so as to contact said pressing member, after the incorporation into the groove, is plastically deformed by the load application from the turbine axial direction outer peripheral side, radially outward of the blade root portion The blade root portion is prevented from rotating by pushing it up .

Furthermore, the third invention is integrally formed at the tip of the blade profile portion and the blade root portion that is inserted into and engaged with the disk grooves provided in the blade rotation direction on the outer peripheral portion of the turbine disk from the turbine axial direction side. The adjacent integral covers by the elastic restoring force of the blade profile portion to be torsionally deformed by being pushed into the turbine disk from the turbine rotating shaft direction side. A turbine blade configured as described above, wherein a groove having a cross-sectional shape having a radially outer end surface and an inner periphery end surface in a blade rotation direction is provided on a turbine disk axial end surface, and a radial height is provided in the groove. the blade root by but incorporate pressing member having a radially outer peripheral surface and inner peripheral surface to decrease gradually in the direction of insertion into the circumferential direction, integration into the groove of the pressing member The pushing up radially outwardly, characterized in that to prevent rotation of the blade root.

The fourth invention is the turbine equipment provided with a turbine rotor blade according to any one the first to third.

  According to the turbine rotor blade of the present invention, opposed to the inner diagonal pressing force generated between the blade root portion and the disk groove forming the disk groove between the blade root portion of the turbine rotor blade and the disk groove, Since a member that pushes back the blade root portion is provided, it is possible to prevent contact between the blade root portion and the disk groove engaging portion, and high reliability that high stress does not act on the blade root portion and the disk groove engaging portion is high. Turbine blades can be provided.

  Further, according to the turbine equipment of the present invention, along with the improvement of the reliability of the turbine rotor blade, the equipment can be operated for a long time, and the working efficiency is improved.

Hereinafter, an embodiment of a turbine rotor blade of the present invention will be described with reference to the drawings.
1 and 2 show a first embodiment of a turbine rotor blade of the present invention, and FIG. 1 shows a part of an annular blade row formed by the first embodiment of a turbine rotor blade of the present invention. FIG. 2 is a cross-sectional view of the first embodiment of the turbine rotor blade of the present invention viewed from the direction of arrows II-II shown in FIG.
1 and 2, a turbine rotor blade 1 includes a blade profile portion 2, a blade root portion 3 of the blade profile portion 2, a blade root portion 4 provided on the blade root portion 3, a turbine disk 5, An integral cover integrally formed at the tip of the blade profile portion 2 and a disk groove 6 provided in the outer peripheral portion of the turbine disc 5 in the blade rotation direction and engaged with the blade root portion 4 inserted from the turbine rotation axis direction side. 7.

  The blade root portion 4 and the disk groove 6 are tapered toward the inner side, respectively, and the engagement portion between the blade root portion 4 and the disk groove 6 is on the engagement surface thereof in the turbine rotational axis direction. And a plurality of engaging protrusions arranged in the radial direction.

  The turbine rotor blades 1 are sequentially assembled from the turbine axial direction side into a disk groove 6 provided in the turbine disk 5, and a plurality of turbine rotor blades 1 are attached to the turbine disk 5 in the blade rotation direction to constitute an annular blade row.

  Grooves 8 that are concentric with the axial center of the turbine rotating shaft and that extend in the axial direction of the turbine rotating shaft are formed in the inner part (lower part) of the disk groove 6 on the axial end surface of the turbine disk 5. . As shown in FIG. 2, the groove 8 includes a radially outer peripheral surface 81 located on the radially outer peripheral side of the radially innermost surface of the disk groove 6 and a radially innermost peripheral surface of the disk groove 6. And a circumferential surface 82 on the radially inner peripheral side which is located on the radially inner peripheral side. The peripheral surface 81 on the radially outer peripheral side described above is partially interrupted by the disk groove 6.

  On the inlet side outlet side end surface on the radially inner peripheral side of the blade root portion 4, when the blade 1 is inserted, the peripheral surface on the radially outer peripheral side that forms the groove 8 in a state where the blade 1 is pushed up to the radially outer peripheral side. A notch 42 is provided to form a peripheral surface 41 that substantially matches 81.

  A plurality of pressing members 9 having a cross-sectional shape that substantially matches the cross-sectional shape of the groove 8 are inserted into the groove 8 along the circumferential direction. After the pressing member 9 is inserted into the groove 8, the pressing member 9 is fixed to the turbine disk 5 by fixing means such as caulking or welding in order to prevent the pressing member 9 from falling off.

  Further, the pressing member 9 brings the blade root portion 4 to the radially outer peripheral side by contact between the outer peripheral surface 91 on the outer peripheral side in the radial direction and the peripheral surface 41 formed by the notch portion 42 provided in the blade root portion 4. By pressing, the rotation of the wing 1 is suppressed. As a result, the one-sided contact that has occurred at the engaging portion between the blade root portion 4 and the disk groove 6 is prevented. Further, the pressing member 9 also has a function as a holding jig when machining the outer peripheral surface of the integral cover 7 after the blade 1 is assembled.

Next, the operation of the above-described first embodiment of the turbine rotor blade of the present invention will be described with reference to FIGS.
The turbine rotor blades 1 are assembled by sequentially implanting them in the disk grooves 6 and sequentially implanting M blades on the entire circumference up to the last (Mth) turbine blade 1.

  First, the first turbine blade 1 is inserted into the disk groove 6 to a predetermined position. Next, the pressing member 9 is inserted. By inserting the pressing member 9 into the groove 8, the turbine rotor blade 1 is pushed up to the radially outer peripheral side. Similarly, the second turbine blade is inserted into the disk groove 6 to a predetermined position, and the pressing member 9 is inserted into the groove 8. This is repeated until the last (Mth) turbine blade, and the blades of the entire circumference are implanted.

  As described above, when the configuration in which the pressing member 9 is not inserted into the groove 8 is adopted, the blade rotation direction pitch of the integral cover 7 is the geometric pitch (the end face of the integral cover 7 facing the blade rotation direction is the turbine surface). The pitch is inclined with respect to the rotation axis direction and is larger than the pitch of one blade obtained by dividing the circumferential length of the mounting radius position of the integral cover 7 by the number of blades attached in the circumferential direction. All the turbine blades 1 are constrained by contact between adjacent integral covers 7 and the blades 1 are torsionally deformed. At the same time, the blade root portion 3 and the blade root portion 4 try to rotate around the axis thereof. Since the blade root portion 4 and the disk groove 6 are usually provided with a gap, the blade root portion 4 rotates in the circumferential direction with respect to the disk groove 6 due to the shape of the engaging portion of the disk groove 6. When the turbine rotates and centrifugal force acts while the blade root portion 4 is rotated, the blade root portion 4 is supported by a part of the axial end side end surface and the outlet end surface of the disk groove 6 and is very high. Although there is a possibility that stress is generated, this is solved by inserting the above-described pressing member 9 into the groove 8.

  That is, when the pressing member 9 is inserted into the groove 8, the peripheral surface 81 on the radially outer peripheral side of the pressing member 9 comes into contact with the peripheral surface 41 formed by the notch portion 42 provided in the blade root portion 4, and the blade root portion 4 is pushed up radially outward against the pressing force in the inner diagonal direction generated at the engaging portion between the blade root 4 and the disk groove 6 to prevent the blade root 4 from rotating. As a result, it is possible to prevent the engagement portion between the blade root portion 4 and the disk groove 6 from coming into contact with each other and maintain the engagement state of the engagement portion appropriately.

  Further, the pressing member 9 functions as a holding jig at the time of machining the outer peripheral surface of the integral cover 7 after the wing 1 is assembled. Although the outer peripheral surface of the cover 7 is extracted after machining, in the present invention, the pressing member 9 is not required to be extracted. Work time is shortened and storage management of the holding jig is not necessary.

  As described above, according to the present embodiment, rotation of the blade root 4 of the turbine rotor blade 1 can be prevented, adjacent integral covers 7 can be reliably connected, and the blade root 4 can be connected to the blade root 4 by centrifugal force. The acting stress can be reduced, and high reliability can be ensured.

  3 and 4 show a second embodiment of the turbine rotor blade of the present invention, and FIG. 3 shows a part of the turbine rotor blade constituting the second embodiment of the turbine rotor blade of the present invention. FIG. 4 is a perspective view showing another example of the pressing member used in the second embodiment of the turbine rotor blade of the present invention shown in FIG. 3. In these drawings, the same parts as those shown in FIGS. 1 and 2 are denoted by the same reference numerals as those in FIGS. 1 and 2, and the description thereof is omitted.

  As in the first embodiment of the present invention described above, the second embodiment of the present invention prevents the engagement of the blade root portion 4 and the disk groove 6 due to the pressing member 9, and The work for fixing the pressing member 9 to the groove 8 is reduced, and the pressing member 9 is formed in an inverted L-shaped cross section as shown in FIG.

  That is, the pressing member 9 is formed by cutting out the inner peripheral portion of the end surface on one side and between the peripheral surface 91 on the radially outer peripheral side and the peripheral surface 92 on the radially inner peripheral side. Another inner peripheral surface 93 set to a dimension h1 smaller than the radial dimension h2 is provided. With this configuration, the portion protruding radially inward from the peripheral surface 93 exhibits a retaining function by engaging with the groove 8.

  On the turbine disk 5 side, a groove 8 having a similar cross-sectional shape is formed so that the pressing member 9 is fitted as shown in FIG. Further, in order to enable the pressing member 9 to be fitted from the turbine rotation axis direction, a radial dimension corresponding to the radial dimension h2 of the pressing member 9 is connected to the groove 8 at a part of the circumferential direction of the turbine disk 5. The notch part 10 which has is formed.

  Next, the operation of the above-described second embodiment of the turbine rotor blade of the present invention will be described with reference to FIGS.

  The turbine rotor blades 1 are assembled by sequentially implanting in the disk grooves 6 and sequentially implanting M blades on the entire circumference up to the last (M-th) turbine rotor blade.

  First, the first turbine blade is inserted into the disk groove 6 to a predetermined position. Next, the pressing member 9 is inserted into the groove 8 from the notch 10 provided at one location of the groove 8, and the pressing member 9 is circled to the bottom of the blade root 4 of the first turbine blade. Move in the circumferential direction. By inserting the pressing member 9, the turbine rotor blade 1 is pushed up radially outward. Similarly, the second turbine blade is inserted into the disk groove 6 to a predetermined position, and the pressing member 9 is inserted into the groove 8 in the same manner as described above.

  This is repeated until the last (Mth) turbine blade and the blades of the entire circumference are implanted. At this time, although the final pressing member 9 is located in the notch 10, the pressing member 9 is caulked, welded, or the like in order to prevent the dropout as in the first embodiment described above. It is fixed to the turbine disk 5 by fixing means.

  According to this embodiment, the rotation of the blade root portion 4 of the turbine rotor blade 1 can be prevented, adjacent integral covers 7 can be reliably connected, and the stress acting on the blade root portion 4 due to centrifugal force can be reduced. And high reliability can be ensured.

  Further, the pressing member 9 functions as a holding jig at the time of machining the outer peripheral surface of the integral cover 7 after the blade 1 is assembled, and is used by being assembled to the turbine disk 5, so that the extraction work can be set up. This eliminates the need for the assembling operation time, and does not require storage management of the holding jig.

  Furthermore, since the pressing member 9 is reliably engaged with the groove 8, it is possible to prevent the pressing member 9 from falling off the groove 8.

  5 and 6 show a third embodiment of the turbine rotor blade of the present invention. FIG. 5 is a side view of the third embodiment of the turbine rotor blade of the present invention viewed from the turbine axial direction side. 6 and 6 are perspective views showing still another example of the pressing member used in the third embodiment of the turbine rotor blade of the present invention shown in FIG. In these drawings, the same parts as those shown in FIGS. 1 to 4 are denoted by the same reference numerals as those in FIGS. 1 to 4 and description thereof is omitted.

  In the third embodiment of the present invention, as in the first embodiment of the present invention described above, the blade root portion 4 and the disk groove are changed by changing the push-up amount of the pressing member 9 toward the outer peripheral side in the radial direction. 6, and the fixing work of the pressing member 9 to the groove 8 is reduced, and the peripheral surface 91 on the radially outer peripheral side and the inner peripheral side of the pressing member 9 are reduced. As shown in FIG. 6, the circumferential surfaces 92 and 93 are formed such that their height in the radial direction becomes lower in the moving direction, that is, in the circumferential direction (h5 <h6, h5 ′ <h6 ′). .

  According to this embodiment, the pressing member 9 can change the pushing amount of the blade root portion 4 toward the outer peripheral side in the radial direction by setting and adjusting the relative position of the blade root portion 4 and the pushing amount is insufficient. In this case, the pushing-up effect on the blade root 4 can be increased by moving the pushing member 9 in the circumferential direction in the groove 8 until the radial height of the pushing member 9 is increased. The same effects as those of the embodiment described above can be obtained.

  The pressing member 9 is inserted into and fixed to the groove 8 in the same manner as in the above-described embodiment.

  FIG. 7 shows a fourth embodiment of the turbine rotor blade of the present invention, and is a longitudinal sectional view of the fourth embodiment of the turbine rotor blade of the present invention. In this figure, parts similar to those in the previous figures are given the same reference numerals, and description thereof is omitted.

  In this embodiment, the cross-sectional shape of the pressing member 9 is such that the inner circumferential side surface thereof gradually increases in height in the radial direction from the end surface on the turbine axial direction side of the turbine disk 5 toward the inside of the turbine disk 5 (h3 <h4). ) And the cross-sectional shape of the groove 8 is also formed in the same manner. Also in this embodiment, the same effect as that of the above-described embodiment can be obtained.

  FIGS. 8 and 9 show a fifth embodiment of the turbine rotor blade of the present invention, and FIG. 9 shows a part of an annular blade row formed by the fifth embodiment of the turbine rotor blade of the present invention. FIG. 9 is a perspective view showing still another example of the pressing member used in the fifth embodiment of the turbine rotor blade of the present invention shown in FIG. In these drawings, the same parts as those shown in FIGS. 1 to 4 are denoted by the same reference numerals as those in FIGS. 1 to 4, and the description thereof is omitted.

  In this embodiment, the cross-sectional shape of the pressing member 9 and the groove 8 into which the pressing member 9 is fitted is formed in a horizontal T shape. That is, a protruding portion 94 is provided on one side surface of the pressing member 9, and the radial outer peripheral surface 95 of the protruding portion 94 is brought into contact with the peripheral surface 41 formed on the blade root portion 4, thereby It is configured to push upward.

  In this embodiment, the radial outer peripheral surface 91 of the pressing member 9 or the radial outer peripheral surface 95 of the protruding portion 94 is formed as an inclined surface in the circumferential direction so that the blade root portion 4 is pushed outward in the radial direction. It is also possible to adjust the lifting force.

  According to this embodiment, the same effect as that of the above-described embodiment can be obtained. Further, since the pressing member 9 is prevented from coming off in the axial direction by the two upper and lower portions, the occurrence of failure due to the drop-off can be minimized, and the reliability is improved.

  FIG. 10 shows the sixth embodiment of the turbine rotor blade of the present invention. In FIG. 10, the same parts as those in the previous drawings are denoted by the same reference numerals, and description thereof is omitted.

  In this embodiment, after assembling the pressing member 9 into the groove 8, a gap is generated between the groove 8 and the pressing member 9, and it is insufficient to restrain the movement of the blade root portion 4 toward the radially inner peripheral side. It provides a strategy that works effectively in some cases. That is, the pressing member 9 is rolled up from the turbine axial direction side, that is, a larger load F is applied to the axial end side surface of the turbine disk 5 in the pressing member 9 than the turbine axial direction side to By plastically deforming in the axial direction and the radially outer peripheral side, the effect of pushing up the blade root portion 4 is increased and the rotation of the blade root portion 4 is prevented.

  Also in this embodiment, the same effect as that of the above-described embodiment can be obtained.

  This embodiment can be applied to each of the embodiments described above.

  FIG. 11 is a front view showing in partial cross section turbine equipment to which each embodiment of the turbine rotor blade of the present invention is applied. In this turbine equipment, as shown in FIG. 11, a moving blade cascade 110 in which each embodiment of the turbine moving blade according to the present invention described above is formed in an annular shape has a stationary blade on the inner wall of a stationary body such as a casing 111, for example. Are alternately arranged in the turbine axial direction between the stationary blade cascades 112 formed in a ring shape. Generally, the stationary blade cascade 112 and the moving blade cascade 110 adjacent in the axial direction are set as one paragraph, and a plurality of such paragraphs are provided.

  According to the turbine equipment to which each embodiment of the turbine rotor blade of the present invention is applied, the equipment can be operated for a long period of time and the working efficiency is improved as the reliability of the turbine rotor blade is improved.

  In addition, although the steam turbine was illustrated in FIG. 11 as an application object of the turbine rotor blade of this invention, of course, it is applicable also to a gas turbine. Further, the present invention can be applied to a high pressure stage, an intermediate pressure stage, or a low pressure stage, but it is particularly effective when applied to a high / intermediate pressure stage having a short blade length.

It is the front view which looked at a part of annular ring cascade which constitutes a 1st embodiment of a turbine bucket of the present invention from the turbine rotating shaft direction. It is sectional drawing of 1st Embodiment of the turbine rotor blade of this invention from the II-II arrow line shown in FIG. It is the side view which looked at a part of turbine bucket which constitutes a 2nd embodiment of a turbine bucket of the present invention from the circumference direction. It is a perspective view which shows the other example of the press member used for 2nd Embodiment of the turbine rotor blade of this invention shown in FIG. It is the side view seen from the turbine axial direction side of 3rd Embodiment of the turbine rotor blade of this invention. It is a perspective view which shows the further another example of the press member used for 3rd Embodiment of the turbine rotor blade of this invention shown in FIG. It is a longitudinal cross-sectional view of 4th Embodiment of the turbine rotor blade of this invention. It is the side view which looked at a part of cyclic | annular blade cascade which comprises 5th Embodiment of the turbine rotor blade of this invention from the turbine rotating shaft direction. It is a perspective view which shows the other example of the press member used for 5th Embodiment of the turbine rotor blade of this invention shown in FIG. It is a longitudinal cross-sectional view of 6th Embodiment of the turbine rotor blade of this invention. It is a side view which shows the turbine equipment to which each embodiment of the turbine rotor blade of this invention is applied in a partial cross section.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Turbine blade 2 Blade profile part 3 Blade root part 4 Blade root part 5 Turbine disk 6 Disc groove 7 Integral cover 8 Groove 9 Pressing member 41 Circumferential surface 42 Notch

Claims (4)

A blade root portion inserted into and engaged with a plurality of disk grooves provided in the blade rotation direction on the outer peripheral portion of the turbine disk from the turbine axial direction side, and an integral cover integrally formed at the tip of the blade profile portion. A turbine blade configured to contact and restrain adjacent integral covers by elastic restoring force of the blade profile portion to be torsionally deformed by being pushed into the turbine disk from the turbine rotating shaft direction side. , A groove provided in the turbine disk axial direction inlet side and outlet side end face along the blade rotation direction through the lower part of the disk groove, and a radial outer periphery of the groove on the tip end side face of the blade root portion pushed into the disk groove The radially inner peripheral surface provided to substantially coincide with the surface and the radially outer peripheral surface abut on the radially inner peripheral surface of the blade root portion. A pressing member incorporated in the turbine disk, and a notch portion provided on an end surface of the turbine disk and capable of inserting the pressing member into the groove from the turbine rotating shaft direction side, and the groove and the pressing incorporated in the groove member comprises a cross-sectional shape having a radially outer end face and the inner peripheral end face, the pressing member is provided with a radial outer peripheral surface and the inner peripheral surface of the radial height is reduced gradually in the insertion direction of the circumferential direction Turbine blades characterized by that.   A blade root portion inserted into and engaged with a plurality of disk grooves provided in the blade rotation direction on the outer peripheral portion of the turbine disk from the turbine axial direction side, and an integral cover integrally formed at the tip of the blade profile portion. A turbine rotor blade configured to contact and restrain adjacent integral covers by elastic restoring force of the blade profile portion to be torsionally deformed by being pushed into the turbine disk from the turbine rotating shaft direction side. , A groove provided in the turbine disk axial direction inlet side and outlet side end face along the blade rotation direction through the lower part of the disk groove, and a radial outer periphery of the groove on the tip end side face of the blade root portion pushed into the disk groove The radially inner peripheral surface provided so as to substantially coincide with the surface, and the radially outer peripheral surface abut on the radially inner peripheral surface of the blade root portion. A pressure member incorporated in the groove, and the pressure member is plastically deformed by applying a load from the outer peripheral side in the turbine axial direction after being assembled into the groove, and pushes the blade root portion outward in the radial direction. Turbine blades characterized by preventing rotation of the rotor. A blade root portion inserted into and engaged with a plurality of disk grooves provided in the blade rotation direction on the outer peripheral portion of the turbine disk from the turbine axial direction side, and an integral cover integrally formed at the tip of the blade profile portion. A turbine rotor blade configured to contact and restrain adjacent integral covers by elastic restoring force of the blade profile portion to be torsionally deformed by being pushed into the turbine disk from the turbine rotating shaft direction side. The turbine disk axial end face is provided with a groove having a cross-sectional shape having a radial outer peripheral end face and an inner peripheral end face in the blade rotation direction, and the radial height of the groove in the insertion direction in the circumferential direction is provided. built pressing member having a radially outer peripheral surface and inner peripheral surface to decrease gradually, press the blade root portion radially outward by integration into the groove of the pressing member Up, the turbine blade, characterized in that to prevent rotation of the blade root. A turbine equipment comprising the turbine rotor blade according to any one of claims 1 to 3.

Images