WO2019008724A1 - Turbine - Google Patents

Turbine Download PDF

Info

Publication number
WO2019008724A1
WO2019008724A1 PCT/JP2017/024809 JP2017024809W WO2019008724A1 WO 2019008724 A1 WO2019008724 A1 WO 2019008724A1 JP 2017024809 W JP2017024809 W JP 2017024809W WO 2019008724 A1 WO2019008724 A1 WO 2019008724A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
heat shield
rotor
hole
turbine rotor
Prior art date
Application number
PCT/JP2017/024809
Other languages
English (en)
Japanese (ja)
Inventor
悟 関根
秀幸 前田
Original Assignee
東芝エネルギーシステムズ株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 東芝エネルギーシステムズ株式会社 filed Critical 東芝エネルギーシステムズ株式会社
Priority to PCT/JP2017/024809 priority Critical patent/WO2019008724A1/fr
Publication of WO2019008724A1 publication Critical patent/WO2019008724A1/fr

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means

Definitions

  • Embodiments of the present invention relate to a turbine.
  • turbines In recent years, in power generation plants using axial flow turbines (hereinafter simply referred to as “turbines”) such as steam turbines and gas turbines, it has been practiced to raise the turbine inlet temperature to improve power generation efficiency. .
  • a heat shield structure is required to protect the turbine rotor and the turbine blades from the high temperature working fluid.
  • the turbine rotor is protected from the high temperature working fluid leaking from the main flow path of the turbine by surrounding the outer peripheral surface of the turbine rotor with the heat shield plate of the heat shield member.
  • the above heat shield member is engaged with a rotor groove formed in the circumferential direction on the outer peripheral surface of the turbine rotor so as not to come off the turbine rotor. Since the heat shield slides along the rotor groove, a detent structure is required to prevent circumferential movement of the heat shield. Then, after installing a heat shield member in the predetermined position of a turbine rotor, it is possible to attach an anti-rotation structure to the outer side of a heat shield board.
  • the anti-rotation structure may be melted and damaged due to exposure to a high temperature working fluid during operation of the turbine, and the anti-rotation function may be degraded.
  • the problem to be solved by the present invention is to provide a turbine which can prevent the anti-rotation structure from being damaged by the high temperature working fluid and prevent the deterioration of the anti-rotation function.
  • the turbine according to the embodiment includes a turbine rotor, a plurality of turbine blades provided on the turbine rotor, a plurality of heat shield members provided along the circumferential direction on the turbine rotor, and the heat shield members. And a detent structure that prevents sliding along a rotor groove formed in the turbine rotor.
  • Each of the heat shield members has a heat shield plate, and a leg portion that supports the heat shield plate and that engages with the rotor groove.
  • the anti-rotation structure is provided closer to the turbine rotor than an outer surface of the heat shield plate.
  • the present invention it is possible to provide a turbine capable of preventing the anti-rotation structure from being damaged by a high temperature working fluid and preventing the deterioration of the anti-rotation function.
  • FIG. 2 is a cross-sectional view of a turbine used in the power plant of FIG. 1; It is a partial cross section figure of the turbine concerning a 1st embodiment.
  • FIG. 2 is a partial plan view of a rotor groove formed in a turbine rotor according to the first embodiment.
  • FIG. 5 is a cross-sectional view taken along the line X1-X1 of FIG. 4; It is sectional drawing for demonstrating the installation method to the turbine rotor of the heat-insulation member which concerns on 1st Embodiment. It is sectional drawing for demonstrating the installation method to the turbine rotor of the heat-insulation member which concerns on 1st Embodiment.
  • FIGS. 1 and 2 a schematic configuration of a power plant 100 and a turbine 1 will be described with reference to FIGS. 1 and 2.
  • the power plant 100 supplies an oxygen producing apparatus 110 for extracting oxygen from air by removing nitrogen, a combustor 120 for producing combustion gas, and the produced combustion gas as a working fluid. And a turbine 1.
  • the oxygen extracted by the oxygen generator 110 is supplied to the combustor 120 among them.
  • the combustor 120 burns the supplied oxygen and fuel to generate combustion gas.
  • the fuel used in the combustor 120 includes, for example, nitrogen-free natural gas such as methane gas. Since air from which nitrogen is removed, that is, oxygen is used to burn the fuel, the combustion gas generated in the combustor 120 contains CO 2 gas and water vapor. In addition, a part of regeneration gas (specifically CO2 gas) heated from the regeneration heat exchanger 140 mentioned later is supplied to the combustor 120.
  • the combustion gas generated by the combustor 120 is supplied to the turbine 1 as a working fluid, performs work on a turbine moving blade 20 described later, and rotationally drives the turbine rotor 10.
  • a generator 130 is connected to the turbine 1, and power generation by the generator 130 is performed by rotationally driving the turbine 1.
  • the combustion gas discharged from the turbine 1 is sent to a regenerative heat exchanger 140 provided on the downstream side of the turbine 1.
  • a relatively low temperature regeneration gas is supplied to the regeneration heat exchanger 140 from a CO 2 pump 170 described later.
  • the regenerative heat exchanger 140 the regenerative gas and the exhaust gas exchange heat, and the relatively high temperature exhaust gas is cooled.
  • the cooled exhaust gas is sent to the cooler 150 to be further cooled.
  • the exhaust gas cooled by the cooler 150 is sent to a moisture separator 160 provided downstream of the cooler 150.
  • the moisture separator 160 separates and removes the moisture of the exhaust gas.
  • water is removed from the exhaust gas containing CO 2 and water, and the exhaust gas is regenerated.
  • the regeneration gas regenerated by the moisture separator 160 is sent to the CO 2 pump 170 to increase the pressure of the regeneration gas.
  • the compressed regeneration gas is supplied to the regeneration heat exchanger 140 described above. A portion of the regeneration gas heated by the regeneration heat exchanger 140 is supplied to the combustor 120. The remainder is supplied to the turbine 1 and used as a cooling medium.
  • power generation is performed using high temperature combustion gas (for example, 1000 ° C. or higher) containing CO 2 and water generated by combustion as components, and most of the CO 2 is It is reused.
  • high temperature combustion gas for example, 1000 ° C. or higher
  • the turbine 1 an example of a high pressure turbine having a relatively high pressure of combustion gas is shown.
  • the turbine 1 includes a turbine rotor 10 connected to a generator 130 and a double casing 50.
  • the double casing 50 has an outer casing 51 connected to the gas supply pipe 2 and a casing 52 provided inside the outer casing 51.
  • the combustion gas generated in the combustor 120 is supplied as the working fluid to the most upstream turbine stage 5 via the inlet sleeve 3 a and the nozzle box 3 b provided in the double casing 50.
  • a plurality of turbine nozzles 53 are fixed inside the casing 52, and the turbine rotor 10 is rotatably provided.
  • a plurality of turbine blades 20 are fixed to the turbine rotor 10.
  • the turbine nozzles 53 and the turbine blades 20 are alternately arranged in the rotational axis direction of the turbine rotor 10.
  • One turbine stage 5 is configured by the pair of turbine nozzles 53 and the turbine moving blades 20.
  • a plurality of turbine stages 5 are provided in the rotation axis direction of the turbine rotor 10.
  • the turbine rotor 10 As the working fluid supplied through the gas supply pipe 2 passes through the turbine stage 5, the turbine rotor 10 is rotationally driven. The working fluid that has passed through the downstreammost turbine stage 5 is discharged to the outside of the turbine 1 through the exhaust flow path 4.
  • FIG. 3 is a partial cross-sectional view of the most upstream turbine stage in the turbine according to the first embodiment.
  • the other turbine stages also have an anti-rotation structure similar to that of the most upstream turbine stage.
  • the turbine 1 includes a turbine rotor 10 extending along a rotation axis, and a plurality of turbine blades 20 provided on the turbine rotor 10 at predetermined intervals in the rotation axis direction. And a plurality of heat shielding members 30 provided along the circumferential direction on the turbine rotor 10.
  • a turbine rotor 10 extending along a rotation axis
  • a plurality of turbine blades 20 provided on the turbine rotor 10 at predetermined intervals in the rotation axis direction.
  • a plurality of heat shielding members 30 provided along the circumferential direction on the turbine rotor 10.
  • the turbine rotor 10 has a rotor main body portion 11 and a plurality of rotor disk portions 12 which are provided so as to be projected at predetermined intervals in the rotational axis direction.
  • a rotor groove 10 a for attaching the heat shield member 30 to the rotor main body 11 is formed on the entire circumference of the turbine rotor 10.
  • the rotor groove 10 a is circumferentially formed on the outer peripheral surface 10 s of the rotor main body 11.
  • the rotor groove 10a is provided with a notch 10b for introducing the heat shield member 30 into the rotor groove 10a.
  • an engaged portion 10 c for engaging with the engaging portion 32 a of the leg portion 32 is provided inside the rotor groove 10 a.
  • the turbine rotor 10 is provided with an introduction passage C1 for introducing a high-pressure cooling medium into the cooling chamber S1 and a discharge passage C2 for discharging the cooling medium from the cooling chamber S2.
  • the introduction flow path C1 is a flow path that connects the outside of the turbine rotor 10 to the cooling chamber S1, and for example, introduces the cooling medium supplied from the regenerative heat exchanger 140 described in FIG. 1 into the cooling chamber S1.
  • the turbine rotor 10, the heat shield member 30 and the like are cooled by the cooling medium introduced into the cooling chambers S1 and S2.
  • the heat shielding member 30 has one or more flow paths (not shown) connecting the cooling chamber S1 and the cooling chamber S2. It is provided.
  • the discharge passage C2 brings the cooling chamber S2 into communication with the turbine bucket cooling passage C4.
  • the cooling medium discharged from the cooling chamber S2 to the discharge flow passage C2 cools the turbine moving blade 20 through the turbine moving blade cooling flow passage C4 provided in the turbine moving blade 20 of the next stage, and then the working fluid Discharged into the main flow path of the
  • a turbine moving blade cooling flow passage C3 for connecting the cooling chamber S1 and the main flow passage of the working fluid is provided.
  • a plurality of turbine blades 20 are provided on the rotor disk portion 12. More specifically, the base end of the turbine rotor blade 20 is provided with a planted portion 20a, and by engaging the planted portion 20a with a mounting groove formed on the outer peripheral surface of the rotor disk portion 12, each turbine rotor blade 20 is provided. Are fixed to the rotor disk portion 12.
  • a snubber 20b for suppressing vibration is provided at the tip of the turbine rotor blade 20, a snubber 20b for suppressing vibration is provided.
  • a seal fin 54 for reducing the leakage of the working fluid is provided on the inner peripheral surface of the casing 52 facing the snubber 20b.
  • the turbine nozzle 53 is provided on the inner peripheral surface of the casing 52 so as to be located between the turbine blades 20 adjacent to each other.
  • the turbine nozzle 53 forms, together with the turbine rotor blade 20, an annular main flow path through which the working fluid flows.
  • a seal fin 55 for reducing leakage of the working fluid is provided at the tip of the turbine nozzle 53 facing the heat shield plate 31.
  • the heat shield member 30 has a heat shield plate 31 provided between the turbine nozzle 53 and the rotor main body 11, and a leg 32 for supporting the heat shield plate 31.
  • the legs 32 engage with a rotor groove 10 a formed in the turbine rotor 10. More specifically, the engaging portion 32a of the leg 32 engages with the engaged portion 10c of the rotor groove 10a.
  • a plurality of heat shield members 30 are attached to the rotor groove 10 a so as to surround the outer peripheral surface of the turbine rotor 10, thereby forming a heat shield structure for protecting the turbine rotor 10 from high temperature working fluid leaking from the main flow path of the turbine 1 Be done. That is, the turbine rotors 10 exposed between the turbine moving blades 20 are surrounded by the heat shield plates 31 of the plurality of heat shield members 30 with a cooling space therebetween.
  • the cooling space is divided into a cooling chamber S ⁇ b> 1 and a cooling chamber S ⁇ b> 2 by partition walls formed by the legs 32 of the plurality of heat shields 30.
  • the heat shield member 30 is provided with one or more flow paths (not shown) for communicating the cooling chamber S1 with the cooling chamber S2.
  • the flow path may be provided to the heat shield plate 31 or may be provided to the leg 32. In the former case, the flow path may be provided linearly along the rotation axis of the turbine rotor 10 or may be provided to meander with respect to the rotation axis.
  • the turbine 1 is provided with a detent structure configured to prevent the heat shield member 30 from sliding along the rotor groove 10a.
  • the heat blocking structure is provided closer to the turbine rotor 10 than the outer surface 31 a of the heat shield plate 31 (that is, inside the outer surface 31 a).
  • the anti-rotation structure of the present embodiment has a configuration in which the convex portion and the concave portion provided on the inner side of the outer surface 31 a of the heat shield plate 31 are engaged with each other. Specifically, as shown in FIG. 3, FIG. 6 and FIG. 7, it is provided in a recess 30 c provided in the side surface 31 b of the heat shield plate 31 and a side surface 20 s of the turbine rotor blade 20 adjacent to the heat shield member 30. , And the convex part 21 engaged with the concave part 30c.
  • the heat shielding member 30 is fixed so as not to rotate with respect to the turbine moving blade 20 by inserting the convex portion 21 of the turbine moving blade 20 into the recess 30 c of the heat shielding member 30.
  • FIG. 6 is a cross-sectional view taken along the line X1-X1 of FIG. 4 with the heat shield member 30 inserted in the notch 10b of the rotor groove 10a.
  • 7 is a cross-sectional view taken along line X2-X2 of FIG. 4 in the state.
  • the recess 30c of the heat shield 30 is provided in each of the plurality of heat shields 30 (see FIG. 8).
  • a plurality of convex portions 21 of the turbine moving blade 20 are also provided corresponding to the plurality of concave portions 30 c.
  • the shape of the convex part 21 is rod-shaped, for example, as long as it is a shape corresponding to the recessed part 30c, another shape may be sufficient.
  • a convex part may be provided in the heat-shielding member 30 side, and a recessed part may be provided in the turbine moving blade 20 side. Therefore, generally speaking, the heat blocking structure of the present embodiment includes the heat shielding member 30 and a convex portion provided on one of the turbine moving blades 20 adjacent to the heat shielding member 30, and the heat shielding member And a recess provided on the other of the turbine blades 20 adjacent to the heat shield member 30 and engaged with the protrusion.
  • the recessed part or convex part of the heat shield member 30 may be provided not only in the heat shield plate 31 but in the leg 32.
  • the detent structure (the convex portion 21 and the concave portion 30c) according to the first embodiment does not directly contact the high temperature working fluid flowing in the main flow path of the turbine 1, and the cooling chambers S1 and S2 It is cooled by the filling cooling medium.
  • the anti-rotation structure can be protected from the high temperature working fluid, and the deterioration of the anti-rotation function can be prevented.
  • FIG. 6 is a cross-sectional view of the turbine rotor 10 and the heat shield member 30 in a state in which the last heat shield member 30 is inserted into the rotor groove 10a from the notch 10b.
  • the heat shield member 30 for the entire circumference is slid along the rotor groove 10 a by a half of the circumferential length of the heat shield member 30.
  • the heat insulating member 30 inserted into the rotor groove 10a from the notch 10b is prevented from falling off the notch 10b.
  • the turbine moving blades 20 are fixed to the rotor disk portion 12 as shown in FIG.
  • the turbine rotor blade 20 is fixed by inserting the turbine rotor blade 20 into an embedded groove (not shown) formed in the rotor disk portion 12 and then sliding the turbine rotor blade 20 toward the heat shield member 30 along the embedded groove. It is done by moving it.
  • the convex portion 21 of the turbine rotor blade 20 is inserted into the recess 30c of the heat shield member 30.
  • the heat shield member 30 is prevented from rotating with respect to the turbine rotor 10.
  • the heat blocking structure having the convex portion 21 and the concave portion 30 c is provided closer to the turbine rotor 10 than the outer surface 31 a of the heat shield plate 31. Therefore, the anti-rotation structure does not directly contact the high temperature working fluid flowing in the main flow path of the turbine 1. Furthermore, the anti-rotation structure is cooled by the cooling medium that fills the cooling chambers S1 and S2. Therefore, according to the present embodiment, it is possible to prevent the anti-rotation structure from being damaged by the high temperature working fluid of the turbine, and to prevent the deterioration of the anti-rotation function.
  • FIGS. 11 to 16 a turbine according to a second embodiment of the present invention will be described.
  • One of the differences from the first embodiment of the second embodiment is the configuration of the detent structure.
  • the second embodiment will be described focusing on the differences from the first embodiment.
  • the rotor groove 10 a corresponds to each heat shielding member 30 as shown in FIG. 13.
  • a plurality of detents 10d are provided.
  • the heat blocking structure according to the second embodiment includes a repulsive member 41 that lifts the heat shielding member 30 installed in the rotor groove 10 a to the outer diameter side of the turbine rotor 10, and the heat shielding member 30. And a projection 33 engaged with the detent notch 10d of the rotor groove 10a.
  • FIG. 11 is a cross-sectional view taken along the line X1-X1 of FIG. 13 in a state where the heat shield member 30 is attached to a predetermined position of the rotor groove 10a.
  • the repelling member 41 is attached to the bottom of the leg 32 and disposed between the bottom of the leg 32 and the bottom of the rotor groove 10a.
  • the repulsion member 41 is an elastic body such as a spring, but is not limited to this and may be made of a magnet.
  • a first magnet is provided on the bottom surface of the leg portion 32 of the heat shield member 30, and a second magnet that repels the first magnet is provided on the bottom surface of the rotor groove 10a facing the bottom surface.
  • the protrusion 33 is provided on the leg 32 of the heat shield 30, as shown in FIG.
  • the projection 33 engages with the detent notch 10 d provided in the rotor groove 10 a in a state where the heat shield 30 is lifted by the repulsion member 41.
  • the protrusion 33 is formed to fit the size of the detent notch 10d.
  • the heat shield member 30 is non-rotatably fixed to the turbine rotor 10 by the projection 33 of the heat shield member 30 engaging with the detent notch 10 d of the rotor groove 10 a.
  • the detent structure of the second embodiment is cooled by the cooling medium that fills the cooling chambers S1 and S2 while not being in direct contact with the high temperature working fluid flowing in the main flow path of the turbine 1.
  • the anti-rotation structure can be protected from the high temperature working fluid, and the deterioration of the anti-rotation function can be prevented.
  • the heat blocking structure of this embodiment may be provided about each heat shielding member 30, or may be provided only about the specific heat shielding member 30. As shown in FIG.
  • FIG. 14 is a cross section along line X2-X2 in FIG. 13 in a state where the heat shield member 30 inserted in the rotor groove 10a against the repulsive force of the repulsion member 41 is circumferentially slid to a predetermined position.
  • FIG. FIG. 15 is a cross-sectional view taken along line X1-X1 of FIG. 13 in the state.
  • the pushing force in the radial direction of the turbine rotor 10 is applied to the heat shield member 30 to resist the repulsive force of the repulsion member 41, and the engaging portion 32a of the heat shield member 30 is pushed into the rotor groove 10a from the notch 10b.
  • the heat shield 30 is slid along the rotor groove 10a to a predetermined position while maintaining the pressing force.
  • the heat shield member 30 is lifted by the repulsion member 41, and the projection 33 is fitted in the anti-rotation notch portion 10d.
  • the heat shield member 30 is non-rotatably fixed to the turbine rotor 10.
  • the heat shields 30 for the entire circumference are installed on the turbine rotor 10 in the same manner as for the other heat shields 30.
  • the detent structure including the repulsive member 41 and the projection 33 of the heat shield 30 is provided closer to the turbine rotor 10 than the outer surface 31 a of the heat shield 31. ing. Therefore, the anti-rotation structure does not directly contact the high temperature working fluid flowing in the main flow path of the turbine 1. Furthermore, the anti-rotation structure is cooled by the cooling medium that fills the cooling chambers S1 and S2. Therefore, according to the second embodiment, it is possible to prevent the anti-rotation structure from being damaged by the high temperature working fluid of the turbine, and to prevent the deterioration of the anti-rotation function.
  • the detent structure of the second embodiment can be provided closer to the turbine rotor 10 than the outer surface 31a of the heat shield plate 31. it can. Therefore, according to the second embodiment, the manufacturability and maintainability of the turbine can be improved.
  • the third embodiment will be described focusing on differences from the first embodiment.
  • the bottom of the leg 32 is provided with a hole 32 e (second hole).
  • the heat shield 30 is provided with a through hole 30a having one end opened to the outer surface 31a of the heat shield 31 and the other end opened to the bottom of the hole 32e.
  • the through hole 30 a is a through hole used to insert a tool from the outer surface 31 a side and operate the anti-rotation member 42 from the outside.
  • holes 10e are provided at equal intervals in the circumferential direction on the bottom of the rotor groove 10a.
  • the number of holes 10 e corresponds to the number of heat shielding members 30.
  • the anti-rotation structure of the third embodiment has, as shown in FIG. 17, a repulsive member 41 disposed in the hole 10e of the rotor groove 10a and an anti-rotation member 42 engaged with the hole 10e.
  • FIG. 17 is a cross-sectional view taken along the line X1-X1 of FIG. 19 in a state where the heat shield member 30 is attached to a predetermined position of the rotor groove 10a.
  • the anti-rotation member 42 is lifted by the repelling member 41 toward the outer diameter side of the turbine rotor 10, and is disposed across the hole 10 e and the hole 32 e.
  • the shape of the anti-rotation member 42 is a disk shape, rod shape, or rectangular solid shape, for example, as long as it is a shape corresponding to the hole 10e and the hole 32e, another shape may be sufficient.
  • the length (height) of the anti-rotation member 42 is larger than the depth of the hole 32 e.
  • the heat shield member 30 is non-rotatably fixed to the turbine rotor 10 by arranging the anti-rotation member 42 so as to straddle the hole 10 e and the hole 32 e.
  • the anti-rotation structure of the third embodiment is cooled by the cooling medium that fills the cooling chambers S1 and S2 while not being in direct contact with the high temperature working fluid flowing in the main flow path of the turbine 1.
  • the anti-rotation structure can be protected from the high temperature working fluid, and the deterioration of the anti-rotation function can be prevented.
  • the heat blocking structure of this embodiment may be provided about each heat shielding member 30, or may be provided only about the specific heat shielding member 30. As shown in FIG.
  • FIG. 20 is a cross-sectional view taken along the line X1-X1 of FIG. 19 with the repelling member 41 and the anti-rotation member 42 set in the hole 10e.
  • the repelling member 41 and the anti-rotation member 42 are arranged in this order in each of the plurality of holes 10e provided in the rotor groove 10a. Thereafter, the engaging portion 32 a of the heat shield 30 is inserted into the rotor groove 10 a from the notch 10 b, and the heat shield 30 is slid in the circumferential direction of the turbine rotor 10.
  • the heat shield member 30 interferes with the other heat shield member 42 for the heat shield member 30 before moving to the mounting position, the heat shield member 42 is pushed down using a tool or the like to pass the heat shield member 30 .
  • the anti-rotation member 42 engages with the hole 32e.
  • the tool 90 is inserted into the through hole 30 a of the heat shield member 30, and the heat shield member 30 is allowed to pass by depressing the anti-rotation member 42.
  • the heat shield 30 is non-rotatably fixed to the turbine rotor 10 at a predetermined mounting position.
  • the heat shield members 30 for the entire circumference are installed on the turbine rotor 10 by performing the same method as the above method for the other heat shield members 30.
  • the anti-rotation member 42 is first disposed in all the holes 10 e, but the present invention is not limited to this. That is, whenever the installation work of one heat shielding member 30 is performed, the repulsion member 41 and the anti-rotation member 42 may be arranged in the hole 10 e at the installation position of the heat shielding member 30. According to this method, while sliding the heat shield member 30 to the predetermined position, it is not necessary to press down the other heat shield member 42 for the heat shield member 30 with the tool 90, and the workability can be improved. .
  • the heat blocking structure including the repulsive member 41 and the heat blocking member 42 is provided closer to the turbine rotor 10 than the outer surface 31 a of the heat shield plate 31. Therefore, the anti-rotation structure does not directly contact the high temperature working fluid flowing in the main flow path of the turbine 1. Furthermore, the anti-rotation structure is cooled by the cooling medium that fills the cooling chambers S1 and S2. Thus, according to the third embodiment, it is possible to prevent the anti-rotation structure from being damaged by the high temperature working fluid of the turbine, and to prevent the deterioration of the anti-rotation function.
  • the detent structure of the third embodiment can be provided closer to the turbine rotor 10 than the outer surface 31a of the heat shield plate 31. it can. Therefore, according to the third embodiment, the manufacturability and maintainability of the turbine can be improved.
  • the pushing force in the radial direction of the turbine rotor 10 is continued to be applied to the heat shield member 30 as in the second embodiment. Since it is not necessary, the workability can be improved.
  • the cooling medium introduction hole 30 b may be provided in the leg portion 32 of the heat shield member 30.
  • the cooling medium introduction hole 30b brings the cooling space (cooling chamber S1 in FIG. 23) sandwiched by the heat shield plate 31 and the turbine rotor 10 into communication with the through hole 30a, and the cooling medium in the cooling space to the through hole 30a. Introduce. Thereby, it is possible to prevent the high temperature leaked fluid leaking from the main flow passage of the turbine 1 from entering the through hole 30a. As a result, it can prevent that the heat shield member 30 becomes high temperature.
  • the cooling medium introduction hole 30b may be provided to communicate the cooling chamber S2 with the through hole 30a.
  • the cooling medium introduction hole 30 b may be provided in the heat shield plate 31.
  • the number of cooling medium introduction holes 30b is not limited to one, and may be plural. The size and the number of the diameters of the cooling medium introduction holes 30b are determined in consideration of the leakage fluid, the flow velocity of the cooling medium, and the like.
  • FIGS. 24 to 27 One of the differences from the first embodiment of the fourth embodiment is the configuration of the detent structure.
  • the fourth embodiment will be described centering on differences with the first embodiment
  • a screw hole 10f (a first screw hole) Section) is provided in the bottom surface of the rotor groove 10a.
  • a screw thread is formed on the inner side surface of the screw hole 10f.
  • the number of screw holes 10 f corresponds to the number of heat shielding members 30.
  • FIG. 24 is a cross-sectional view taken along the line X1-X1 of FIG. 26 in a state where the heat shield member 30 is attached to a predetermined position of the rotor groove 10a.
  • screw holes 32 f are provided on the bottom of the legs 32 of the heat shield 30.
  • a screw thread is formed on the inner side surface of the screw hole 32f.
  • the heat shielding member 30 is provided with a through hole 30a.
  • the anti-rotation structure of the fourth embodiment has an anti-rotation member 43 disposed across the screw hole portion 10 f and the screw hole portion 32 f.
  • the anti-rotation member 43 is a male screw having a thread formed on the circumferential surface. Further, a groove or a recess (not shown) for engaging with a tool (driver or the like) inserted into the through hole 30a is provided on the upper surface of the anti-rotation member 43.
  • the shape of the groove is, for example, plus or minus, but is not limited thereto.
  • the anti-rotation member 43 is screwed into both the screw hole 10 f of the rotor groove 10 a and the screw hole 32 f of the leg 32.
  • the length (height) of the anti-rotation member 43 is larger than the depth of the screw hole 32 f. Thereby, even when the anti-rotation member 43 is screwed to the bottom of the screw hole 32f, a part of the anti-rotation member 43 protrudes from the bottom surface of the engaging part 32a, ensuring the anti-rotation function. can do.
  • the heat shield member 30 is non-rotatably fixed to the turbine rotor 10 by arranging the anti-rotation member 43 astride the screw hole portion 10 f and the screw hole portion 32 f as described above.
  • the anti-rotation structure of the fourth embodiment is cooled by the cooling medium that fills the cooling chambers S1 and S2 while not being in direct contact with the high temperature working fluid flowing in the main flow path of the turbine 1.
  • the anti-rotation structure can be protected from the high temperature working fluid, and the deterioration of the anti-rotation function can be prevented.
  • the heat blocking structure of this embodiment may be provided about each heat shielding member 30, or may be provided only about the specific heat shielding member 30. As shown in FIG.
  • the locking member 43 is disposed in each of the plurality of screw holes 10f provided in the rotor groove 10a. More specifically, the anti-rotation member 43 is screwed into the screw hole 10f so that the anti-rotation member 43 does not protrude from the bottom of the rotor groove 10a. Thereafter, the engaging portion 32 a of the heat shield 30 is inserted into the rotor groove 10 a from the notch 10 b, and the heat shield 30 is slid in the circumferential direction of the turbine rotor 10. In the case of the present embodiment, since the heat shield member 30 does not interfere with the other heat blocking member 43 for the heat shield member 30 before moving to the mounting position, the workability is improved.
  • the heat shield 30 After sliding the heat shield member 30 to a predetermined mounting position, a tool such as a driver is inserted from the through hole 30a, and the anti-rotation member 43 is rotated and pulled out from the bottom surface of the rotor groove 10a. At this time, the anti-rotation member 43 is not completely withdrawn from the screw hole 10f, but a part is left in the screw hole 10f.
  • the heat shield 30 is non-rotatably fixed to the turbine rotor 10 at a predetermined mounting position.
  • the heat shields 30 for the entire circumference are installed on the turbine rotor 10 in the same manner as described above for the other heat shields 30.
  • the detent structure having the detent member 43 is provided closer to the turbine rotor 10 than the outer surface 31 a of the heat shield plate 31. Therefore, the anti-rotation structure does not directly contact the high temperature working fluid flowing in the main flow path of the turbine 1. Furthermore, the anti-rotation structure is cooled by the cooling medium that fills the cooling chambers S1 and S2. Therefore, according to the fourth embodiment, it is possible to prevent the anti-rotation structure from being damaged by the high temperature working fluid of the turbine and to prevent the deterioration of the anti-rotation function.
  • the anti-rotation structure of the fourth embodiment can be provided closer to the turbine rotor 10 than the outer surface 31a of the heat shield plate 31. it can. Therefore, according to the fourth embodiment, the manufacturability and maintainability of the turbine can be improved.
  • the anti-rotation member 43 is supported not by the repelling member 41 but by the screw holes 10f and 32f. You can avoid the situation.
  • the cooling medium introduction hole 30 b may be provided in the leg portion 32 of the heat shield 30.
  • the anti-rotation structure according to the fourth embodiment further includes a repulsion member 44 disposed in the screw hole portion 10 f and applying a force on the outer diameter side of the turbine rotor 10 to the anti-rotation member 43. You may have. As a result, it is possible to suppress rotation of the anti-rotation member 43 and non-engagement with the screw hole 10 f or the screw hole 32 f.
  • the repelling member 44 may be an elastic body such as a spring or may be a magnet.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Le problème décrit par la présente invention est de fournir une turbine dans laquelle une structure anti-rotation est empêchée d'être endommagée par un fluide de fonctionnement à haute température, empêchant ainsi une détérioration de la fonction anti-rotation. La solution selon un mode de réalisation de la présente invention porte sur une turbine comprenant: un rotor de turbine; une pluralité d'aubes de rotor de turbine disposées sur le rotor de turbine; une pluralité d'éléments de blocage de chaleur disposés de manière circonférentielle sur le rotor de turbine; et une structure anti-rotation pour empêcher les éléments de blocage de chaleur de glisser le long de rainures de rotor formées dans le rotor de turbine. Les éléments de blocage de chaleur ont des plaques de blocage de chaleur et des pieds, les pieds supportant les plaques de blocage de chaleur et venant en prise avec les rainures de rotor. La structure anti-rotation est disposée plus près du rotor de turbine que les surfaces périphériques externes des plaques de blocage de chaleur.
PCT/JP2017/024809 2017-07-06 2017-07-06 Turbine WO2019008724A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/JP2017/024809 WO2019008724A1 (fr) 2017-07-06 2017-07-06 Turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2017/024809 WO2019008724A1 (fr) 2017-07-06 2017-07-06 Turbine

Publications (1)

Publication Number Publication Date
WO2019008724A1 true WO2019008724A1 (fr) 2019-01-10

Family

ID=64950699

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2017/024809 WO2019008724A1 (fr) 2017-07-06 2017-07-06 Turbine

Country Status (1)

Country Link
WO (1) WO2019008724A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5030853B1 (fr) * 1970-03-30 1975-10-04
JPS54141908A (en) * 1978-04-25 1979-11-05 Toshiba Corp Steam turbine
JPS58100201U (ja) * 1981-12-28 1983-07-07 三菱重工業株式会社 軸流機械の動翼固定装置
JP2003206893A (ja) * 2001-12-21 2003-07-25 Nuovo Pignone Holding Spa 軸流圧縮機のロータブレードを結合しかつ固定するための装置
US20080181778A1 (en) * 2005-08-23 2008-07-31 Alstom Technology Ltd Locking and fixing device for a heat shield element for a rotor unit of a turbomachine
FR2971541A1 (fr) * 2011-02-16 2012-08-17 Snecma Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par depliage d'un u
US20160160649A1 (en) * 2014-12-08 2016-06-09 General Electric Technology Gmbh Rotor heat shield and method for securing the same into a rotor assembly

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5030853B1 (fr) * 1970-03-30 1975-10-04
JPS54141908A (en) * 1978-04-25 1979-11-05 Toshiba Corp Steam turbine
JPS58100201U (ja) * 1981-12-28 1983-07-07 三菱重工業株式会社 軸流機械の動翼固定装置
JP2003206893A (ja) * 2001-12-21 2003-07-25 Nuovo Pignone Holding Spa 軸流圧縮機のロータブレードを結合しかつ固定するための装置
US20080181778A1 (en) * 2005-08-23 2008-07-31 Alstom Technology Ltd Locking and fixing device for a heat shield element for a rotor unit of a turbomachine
FR2971541A1 (fr) * 2011-02-16 2012-08-17 Snecma Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par depliage d'un u
US20160160649A1 (en) * 2014-12-08 2016-06-09 General Electric Technology Gmbh Rotor heat shield and method for securing the same into a rotor assembly

Similar Documents

Publication Publication Date Title
US9400114B2 (en) Combustor support assembly for mounting a combustion module of a gas turbine
US10508557B2 (en) Gas turbine
EP2687681B1 (fr) Appareil d'étanchéité de turbine et système d'énergie thermique
JP5865204B2 (ja) 軸流タービン及び発電プラント
JP6010488B2 (ja) 軸流タービンおよびこれを備えた発電プラント
CN101845996A (zh) 用于在燃气轮机中减少二次空气流的装置和系统
JP2014185633A (ja) ターボ機械の冷却が改善された移行ダクト
KR20060043363A (ko) 자동 밀봉 흐름의 감소 방법
JP5543029B2 (ja) ターボ機械のための内部冷却装置
US10550698B2 (en) Turbine
JP6170341B2 (ja) 再生型ガスタービン燃焼器
US10563529B2 (en) Turbine and turbine stator blade
JP5606781B2 (ja) 冷却グランドを有するタービンエンジン
US20170089205A1 (en) Turbine engine assembly and method of assembling the same
JP5955345B2 (ja) 蒸気タービンを含む熱機関の流体シール構造
JP2004144081A (ja) タービン駆動装置とその冷却方法
WO2019008724A1 (fr) Turbine
JP2014521872A (ja) スラストバランスピストンを備えている蒸気タービン
JP2014074406A (ja) 冷却通路を備えた固体シール
WO2015041753A1 (fr) Joints d'étanchéité nid d'abeilles cannelé
US11111803B2 (en) Sealing structure between turbine rotor disk and interstage disk
JP2015200242A (ja) 軸流タービン
WO2019035178A1 (fr) Rangée d'aubes fixes de turbine et turbine
JP5669769B2 (ja) ガスタービンのシール装置
JP2014080920A (ja) シール装置

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 17916733

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 17916733

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: JP