阅读说明：本技术 一种应用于重型燃气轮机的模化透平转子 (Be applied to heavy gas turbine's modularization turbine rotor ) 是由 孟凡刚 冯永志 赵俊明 于宁 马胜远 由岫 王辉 孙涛 陈奕嘉 郭祖光 戴博林 于 2020-05-20 设计创作，主要内容包括：本发明涉及一种应用于重型燃气轮机的模化透平转子,属于重型燃气轮机技术领域。包括透平前端轴、第一级轮盘、中间盘、第二级轮盘、透平后端轴和短拉杆,所述透平前端轴、第一级轮盘和中间盘依次布置,透平前端轴、第一级轮盘和中间盘通过短拉杆连接,中间盘、第二级轮盘和透平后端轴依次布置,中间盘、第二级轮盘和透平后端轴通过短拉杆连接,透平前端轴、第一级轮盘、中间盘、第二级轮盘、透平后端轴和短拉杆连接后总长度为L1,L1＝995mm。解决现有重型燃气轮机的模化透平转子在高温、高压、高转速及重载环境下,局部易产生裂痕,加工成本高,难度大,转子轮盘易变形断裂,轮盘两两之间装配不稳定的问题。(The invention relates to a modeled turbine rotor applied to a heavy-duty gas turbine, and belongs to the technical field of heavy-duty gas turbines. Including turbine front end axle, first order rim plate, intermediate disk, second level rim plate, turbine rear end axle and short pull rod, turbine front end axle, first order rim plate and intermediate disk are arranged in proper order, and turbine front end axle, first order rim plate and intermediate disk pass through the short pull rod and connect, and intermediate disk, second level rim plate and turbine rear end axle are arranged in proper order, and intermediate disk, second level rim plate and turbine rear end axle pass through the short pull rod and connect, and turbine front end axle, first order rim plate, intermediate disk, second level rim plate, turbine rear end axle and short pull rod connect the back total length and be L1, and L1 is 995 mm. The problem of current heavy gas turbine's modularization turbine rotor under high temperature, high pressure, high rotational speed and heavy load environment, local easy production crack, the processing cost is high, the degree of difficulty is big, the easy deformation fracture of rotor rim plate, the assembly is unstable between two liang of rim plates is solved.)

1. A modular turbine rotor for a heavy duty gas turbine engine, comprising: including turbine front end axle (1), first order rim plate (2), intermediate disk (3), second level rim plate (4), turbine rear end axle (5) and short pull rod (6), turbine front end axle (1), first order rim plate (2) and intermediate disk (3) arrange in proper order, and turbine front end axle (1), first order rim plate (2) and intermediate disk (3) are connected through short pull rod (6), and intermediate disk (3), second level rim plate (4) and turbine rear end axle (5) arrange in proper order, and intermediate disk (3), second level rim plate (4) and turbine rear end axle (5) are connected through short pull rod (6), and turbine front end axle (1), first order rim plate (2), intermediate disk (3), second level rim plate (4), turbine rear end axle (5) and short pull rod (6) are connected the back total length and are L1, and L1 equals 995 mm.

2. A modular turbine rotor for a heavy duty gas turbine according to claim 1, wherein: the turbine front end shaft (1) comprises a first mounting disc (11), a second mounting disc (12), a front end shaft body (13), a boss ring (14), a cone frustum (15) and a wheel disc positioning bulge (16), wherein the first mounting disc (11) is mounted at the left end of the front end shaft body (13), the cone frustum (15) is mounted at the right end of the front end shaft body (13), the second mounting disc (12) is mounted at the right end of the cone frustum (15), the boss ring (14) is arranged at the right end of the second mounting disc (12), a cone inner groove (151) is formed inside the cone frustum (15), the wheel disc positioning bulge (16) is mounted at the bottom of the cone inner groove (151), and a plurality of round holes are uniformly distributed on the first mounting disc (11) and the second mounting disc (12) respectively;

the thickness of the first mounting disc (11) is L101, L101 is 10mm, the outer diameter of the first mounting disc (11) is phi 1, phi 1 is 210mm, a rear end shaft positioning groove is machined in the center of the first mounting disc (11), the diameter and the depth of the rear end shaft positioning groove are phi 2 and L101 respectively, phi 2 is 124mm, 18 first mounting holes (111) are uniformly distributed and machined in the first mounting disc (11), the diameter of each first mounting hole (111) is phi 3, and phi 3 is 11 mm;

the front end shaft body (13) is cylindrical, the thickness of the front end shaft body (13) is L102, L102 is 150mm, the outer diameter of the front end shaft body (13) is phi 4, phi 4 is 150mm, a lightening hole (17) is machined in the center of the front end shaft body (13), the diameter and the depth of the lightening hole (17) are phi 5 and L102 respectively, and phi 5 is 80 mm;

the outer diameter of the left end face of the cone frustum (15) is phi 4, phi 4 is 150mm, the outer diameter of the right end face of the cone frustum (15) is phi 6, phi 6 is 200, the thickness of the cone frustum (15) is L103, L103 is 25mm, a cone inner groove (151) is machined on the right side of the cone frustum (15), the diameter and the depth of the bottom end face of the cone inner groove (151) are phi 7 and L104 respectively, phi 7 is 135mm, and L104 is 12.5 mm;

the wheel disc positioning bulge (16) is arranged at the center of the bottom end face of the conical inner groove (151), the thickness of the wheel disc positioning bulge (16) is L205, L205 is 40.5mm, the outer diameter of the wheel disc positioning bulge (16) is phi 8, phi 8 is 90mm, a wheel disc positioning hole (18) is machined in the right end face of the wheel disc positioning bulge (16), the diameter and the depth of the wheel disc positioning hole (18) are respectively phi 9 and L106, phi 9 is 50mm, and L106 is 28 mm;

the thickness of the second mounting disc (12) is L107, L107 is equal to 10mm, the outer diameter of the first mounting disc (11) is phi 10, phi 10 is equal to 260mm, a conical hole is machined in the center of the second mounting disc (12), the diameter of the right end face of the conical hole is phi 11, phi 11 is equal to 180mm, the conical angle is 90 degrees, 15 second mounting holes (121) are uniformly distributed and machined in the second mounting disc (12), the diameter of the second mounting holes (121) is phi 12, and phi 12 is equal to 11 mm;

the thickness of the boss ring (14) is L108, L108 is 5mm, the inner diameter of the boss ring (14) is phi 11, phi 11 is 180mm, the outer diameter of the boss ring (14) is phi 13, and phi 13 is 190 mm;

first mounting disc (11), second mounting disc (12), front end axis body (13), boss ring (14), circular truncated cone (15) and the protruding (16) of rim plate location process for integrated into one piece, first mounting disc (11), second mounting disc (12), front end axis body (13), boss ring (14), circular truncated cone (15) and the protruding (16) total length of rim plate location are L109, and L109 equals 213 mm.

3. A modular turbine rotor for a heavy duty gas turbine according to claim 2, wherein: the diameter of the first-stage wheel disc (2) is L201, L201 is phi 360mm, the width of the first-stage wheel disc (2) is L203, L203 is 60mm, first stepped shafts (25) are symmetrically machined at the left end and the right end of the first-stage wheel disc (2), the first-stage wheel disc (2) is coaxial with the first stepped shafts (25), the diameter of the first stepped shafts (25) is L202, L202 is phi 260mm, the width of the first stepped shafts (25) is L209, L209 is 20mm, first ports (22) are machined on the coaxial lines of the first stepped shafts (25), and the diameter of the first ports (22) is L206,the width of the first port (22) is L209, L209 is 20mm, a first chamfer (24) is machined on the outer side of the first port (22), the size of the first chamfer (24) is L207, L207 is 2 × 45 degrees, a first central port (23) is machined on the first-stage wheel disc (2) coaxially, the diameter of the first central port (23) is L205, L205 is 50mm, the width of the first central port (23) is L208, L208 is 20mm, a first pull rod hole (21) is machined on the first stepped shaft (25), the first pull rod hole (21) is a through hole with the diameter of L210, L210 is 11mm, the number of the first pull rod holes (21) is N, N first pull rod holes (21) are arrayed on the first stepped shaft (25) by taking the axis of the first-stage wheel disc (2) as the axis, N is 15, the array of the first pull rod holes (21) is L204 mm, and the diameter of L204 is L230 mm.

4. A modular turbine rotor for a heavy duty gas turbine according to claim 3, wherein: the diameter of the intermediate disc (3) is L304, L304 is phi 260mm, the width of the intermediate disc (3) is L305, L305 is 60mm, intermediate pull rod holes (35) are machined in the intermediate disc (3), the number of the intermediate pull rod holes (35) is N, the intermediate pull rod holes (35) are through holes, and the N intermediate pull rod holes (35) are circumferentially arrayed in the middle by taking the axis of the intermediate disc (3) as an axisOn the disc (3), N is 15, the diameter of the circumferential array of the middle pull rod holes (35) is L313, L313 is 230mm, middle stepped shafts (33) are symmetrically machined at two ends of the middle disc (3), the middle disc (3) and the middle stepped shafts (33) are coaxial, the thickness of the middle stepped shafts (33) is L310, L310 is 5mm, the diameter of the middle stepped shafts (33) is L303,the outer diameters of two ends of the intermediate stepped shaft (33) are provided with intermediate chamfers (36), the size of the intermediate chamfers (36) is L306, L306 is 2 × 45 degrees mm, the outer diameter connecting position of the intermediate stepped shaft (33) is provided with an intermediate fillet (37), the size of the intermediate fillet (37) is L307, L307 is R0.5, two ends of the intermediate disc (3) are symmetrically provided with intermediate notches (31), the intermediate disc (3) and the intermediate notches (31) are coaxial, the diameter of the intermediate notches (31) is L302, L302 is 170, the width of the intermediate notches (31) is L312, L312 is 20mm, the intermediate disc (3) is provided with an intermediate central through hole (32) coaxially, the diameter of the intermediate central through hole (32) is L301, L301 is 110mm, the width of the intermediate central through hole (32) is L309, L309 is 20mm, the diameter of the intermediate annular through hole (32) is 20mm, the outer wall of the intermediate disc (3) is provided with an intermediate annular groove (34), the diameter of the intermediate groove (308), the bottom of the intermediate groove (34) is L190 mm, the annular groove (303) is L309 mm, and the bottom of the annular groove (303) is L303).

5. A modular turbine rotor for a heavy duty gas turbine according to claim 4, wherein: the diameter of the second-stage wheel disc (4) is L401, L401 is phi 310mm, the width of the second-stage wheel disc (4) is L403, L403 is 60mm, second stepped shafts (45) are symmetrically machined at the left end and the right end of the second-stage wheel disc (4), the second-stage wheel disc (4) and the second stepped shafts (45) are coaxial, the diameter of the second stepped shafts (45) is L402, L402 is phi 260mm, the width of the second stepped shafts (45) is L409, L409 is 20mm, second ports (42) are machined on the coaxial lines of the second stepped shafts (45), and the diameter of the second ports (42) is L406,the width of the second port (42) is L409, L409 is 20mm, and the outer side of the second port (42)A second chamfer (44) is machined, the size of the second chamfer (44) is L407, L407 is 2 × 45 degrees, a second central port (43) is coaxially machined on the second-stage wheel disc (4), the diameter of the second central port (43) is L405, L205 is 50mm, the width of the second central port (43) is L408, L408 is 20mm, a second pull rod hole (41) is machined in the second stepped shaft (45), the second pull rod hole (41) is a through hole with the diameter of L404, L404 is 11mm, the number of the second pull rod holes (41) is N, N second pull rod holes (41) are circumferentially arrayed on the second stepped shaft (45) by taking the axis of the second-stage wheel disc (4) as an axis, N is 15, the diameter of the circumferential array of the second pull rod holes (41) is L410, and L410 is 230 mm.

6. A modular turbine rotor for a heavy duty gas turbine according to claim 5, wherein: the rear-end shaft (5) of the turbine comprises a conical ring body (51), a long shaft (52), a fixed disc (53) and a ring body (54), wherein the fixed disc (53) is arranged on the outer side of the end face of the conical ring body (51), the ring body (54) is processed on the left end face of the fixed disc (53), the long shaft (52) is arranged at the right end of the conical ring body (51), pull rod holes are uniformly distributed in the fixed disc (53), a conical inner groove (55) is formed in the conical ring body (51), and the cone angle of the conical inner groove (55) is 90 degrees;

the conical ring body (51), the long shaft (52) and the circular ring body (54) are integrally formed, the total length of the conical ring body (51), the long shaft (52) and the circular ring body (54) is L501, and L501 is 635 mm; the thickness of the fixed disc (53) is L502, L502 is 10mm, the outer diameter of the fixed disc (53) is L504, L504 is 260mm, N pull rod holes are uniformly distributed in the fixed disc (53), the diameter of each pull rod hole is L511, L511 is 11mm, N middle pull rod holes are circumferentially arrayed on the fixed disc (53) by taking the axis of the fixed disc (53) as an axis, N is 15, the diameter of each pull rod hole is L513, and L513 is 230 mm; the inner diameter of the torus (54) is L506, L506 is phi 180mm, the outer diameter of the torus (54) is L505, L505 is phi 190mm, the length of the torus (54) is L503, and L503 is phi 5 mm; the distance from the cone vertex of the cone inner groove (55) to the end face of the cone ring body (51) is L510, and L510 is 90 mm; the diameter of the long shaft (52) is L509, L509 is phi 40mm, the right end part chamfer of the long shaft (52) is L508, and L508 is 0.7 multiplied by 45 degrees; the left side outline diameter of the conical ring body (51) is L507, and L507 is phi 200 mm.

7. A modular turbine rotor for a heavy duty gas turbine according to claim 6, wherein: the length of the short pull rod (6) is L601, L601 is 52mm, the diameter of the short pull rod (6) is L602, L602 is phi 10mm, threads (61) are symmetrically machined at two ends of the short pull rod (6), the length of each thread (61) is L603, L603 is 20mm, each thread (61) is M10-6g, a chamfer is machined at the end of each thread (61), the size of each chamfer at the end of each thread (61) is L604, L604 is 0.5 multiplied by 45 degrees, the short pull rod (6) sequentially penetrates through the second mounting hole (121), the first pull rod hole (21) and the middle pull rod hole (35), the threads (61) are connected with the nut, the short pull rod (6) and the nut connect and fix the short pull rod (6) with the second mounting hole (121), the first pull rod hole (21) and the middle pull rod hole (35), and the short pull rod (6) sequentially penetrates through the middle pull rod hole (35), the second pull rod hole (41) and the fixed disc (53), the screw thread (61) is connected with the nut, and the short pull rod (6) and the nut connect, screw and fix the middle pull rod hole (35), the second pull rod hole (41) and the pull rod hole on the fixed disc (53).

Technical Field

The invention relates to a modeled turbine rotor applied to a heavy-duty gas turbine, and belongs to the technical field of heavy-duty gas turbines.

Background

The heavy-duty gas turbine is clean and clean power generation equipment, wherein a rotor is the most main core component, and the design difficulty of the rotor is extremely high due to the fact that the heavy-duty gas turbine works in high-temperature, high-pressure, high-rotating-speed and heavy-load environments. At present, the design and manufacture of the heavy-duty gas turbine rotor in China are in the starting stage, and a few developed countries are in monopoly for the technology. The heavy gas turbine rotor has large axial and radial temperature gradients, different high temperature resistance and strength characteristics at all levels, and the pull rod rotor can well meet the requirements. The design difficulty of the heavy-duty gas turbine pull rod rotor is extremely high, at present, the design and manufacture of the heavy-duty gas turbine rotor in China are in a starting stage, mature modeling models and theories do not exist in China, and a monopoly is laid for the technology in a few developed countries.

The prior modeling turbine rotor of the heavy-duty gas turbine has the following defects in the using process:

1. the rotor works under the environment of high temperature, high pressure, high rotating speed and heavy load, so that the rotor is easy to crack locally in the use process;

2. the processing cost is high, and the processing difficulty is large.

3. The center of the wheel disc is provided with a rotor shaft mounting hole in a conventional mode, and when the wheel disc is used for a long time, the matching mounting positions of the rotor shaft and the wheel disc are stressed intensively, so that deformation and fracture of different degrees occur.

In view of the above technical problems, it is desirable to provide a modeled turbine rotor for a heavy duty gas turbine to solve the above technical problems.

Disclosure of Invention

The invention solves the problems that the modeled turbine rotor of the existing heavy-duty gas turbine is easy to generate cracks locally, has high processing cost and difficulty, is easy to deform and break, and is unstable to assemble between every two rotor discs under the high-temperature, high-pressure, high-rotating-speed and heavy-load environments. The following presents a simplified summary of the invention in order to provide a basic understanding of some aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to determine the key or critical elements of the present invention, nor is it intended to limit the scope of the present invention.

The technical scheme of the invention is as follows:

the utility model provides a be applied to heavy gas turbine's modularization turbine rotor, includes turbine front end axle, first order rim plate, intermediate disc, second level rim plate, turbine rear end axle and short pull rod, turbine front end axle, first order rim plate and intermediate disc are arranged in proper order, and turbine front end axle, first order rim plate and intermediate disc pass through the short pull rod and connect, and intermediate disc, second level rim plate and turbine rear end axle are arranged in proper order, and intermediate disc, second level rim plate and turbine rear end axle pass through the short pull rod and connect, and turbine front end axle, first order rim plate, intermediate disc, second level rim plate, turbine rear end axle and short pull rod connect the back total length and be L1, and L1 equals 995 mm.

Preferably: the turbine front end shaft mounting device comprises a first mounting disc, a second mounting disc, a front end shaft body, a boss ring, a cone frustum and a wheel disc positioning bulge, wherein the first mounting disc is mounted at the left end of the front end shaft body;

the thickness of the first mounting disc is L101, L101 is 10mm, the outer diameter of the first mounting disc is phi 1, phi 1 is 210mm, a rear end shaft positioning groove is machined in the center of the first mounting disc, the diameter and the depth of the rear end shaft positioning groove are phi 2 and L101 respectively, phi 2 is 124, 18 first mounting holes are uniformly distributed and machined in the first mounting disc, the diameter of each first mounting hole is phi 3, and phi 3 is 11 mm;

the front end shaft body is cylindrical, the thickness of the front end shaft body is L102, L102 is 150mm, the outer diameter of the front end shaft body is phi 4, phi 4 is 150mm, a lightening hole is machined in the center of the front end shaft body, the diameter and the depth of the lightening hole are phi 5 and L102 respectively, and phi 5 is 80 mm;

the outer diameter of the left end face of the cone frustum is phi 4, phi 4 is 150mm, the outer diameter of the right end face of the cone frustum is phi 6, phi 6 is 200, the thickness of the cone frustum is L103, L103 is 25mm, a cone inner groove is machined on the right side of the cone frustum, the diameters and the depths of the bottom end faces of the cone inner grooves are phi 7 and L104 respectively, phi 7 is 135mm, and L104 is 12.5 mm;

the wheel disc positioning bulge is arranged at the center of the end face of the bottom of the conical inner groove, the thickness of the wheel disc positioning bulge is L105, the L105 is equal to 40.5, the outer diameter of the wheel disc positioning bulge is phi 8, the phi 8 is equal to 90mm, a wheel disc positioning hole is machined in the right end face of the wheel disc positioning bulge, the diameter and the depth of the wheel disc positioning hole are respectively phi 9 and L106, the phi 9 is equal to 50mm, and the L106 is equal to 28 mm;

the thickness of the second mounting disc is L107, L107 is 10mm, the outer diameter of the first mounting disc is phi 10, phi 10 is 260mm, a conical hole is machined in the center of the second mounting disc, the diameter of the right end face of the conical hole is phi 11, phi 11 is 180mm, the cone angle is 90 degrees, 15 second mounting holes are uniformly distributed and machined in the second mounting disc, the diameter of the second mounting holes is phi 12, and phi 12 is 11 mm;

the thickness of the boss ring is L108, L108 is equal to 5mm, the inner diameter of the boss ring is phi 11, phi 11 is equal to 180mm, the outer diameter of the boss ring is phi 13, and phi 13 is equal to 190 mm;

first mounting disc, second mounting disc, front end axis body, boss ring, circular cone platform and rim plate location are protruding to be the integrated into one piece processing, and first mounting disc, second mounting disc, front end axis body, boss ring, circular cone platform and the protruding total length of rim plate location are L109, and L109 is 213 mm.

Preferably: the diameter of the first-stage wheel disc is L201, L201 is phi 360mm, the width of the first-stage wheel disc is L203, L203 is 60mm, first stepped shafts are symmetrically machined at the left end and the right end of the first-stage wheel disc, the first-stage wheel disc is coaxial with the first stepped shafts, the diameter of the first stepped shafts is L202, L202 is phi 260mm, the width of the first stepped shafts is L209, L209 is 20mm, first ports are machined on the coaxial lines of the first stepped shafts, the diameter of the first ports is L206, L206 is phi +0.046-0mm, the width of the first ports is L209 and L209 mm, first chamfers are machined on the outer sides of the first ports, the size of the first chamfers is L207, L207 is 2 x 45 degrees, first-stage wheel discs are machined coaxially with first central ports, the diameter of the first central ports is L205, L205 mm, phi 50mm, the width of the first central ports is L208 mm, and a first pull rod hole is machined on the first-stage wheel disc, the first pull rod holes are through holes with the diameter of L210, L210 is 11mm, the number of the first pull rod holes is N, the N first pull rod holes are circumferentially arrayed on the first stepped shaft by taking the axis of the first-stage wheel disc (2) as an axis, N is 15, the diameter of the circumferential array of the first pull rod holes is L204, and L204 is phi 230 mm.

Preferably: the diameter of the intermediate disc is L304, L304 is phi 260mm, the width of the intermediate disc is L305, L305 is 60mm, intermediate pull rod holes are machined in the intermediate disc, the number of the intermediate pull rod holes is N, the intermediate pull rod holes are through holes, the N intermediate pull rod holes are circumferentially arrayed on the intermediate disc by taking the axis of the intermediate disc as an axis, N is 15, the diameter of the circumferential array of the intermediate pull rod holes is L313, L313 is phi 230mm, intermediate stepped shafts are symmetrically machined at two ends of the intermediate disc, the intermediate disc and the intermediate stepped shafts are coaxial, the thickness of the intermediate stepped shafts is L310, L310 is 5mm, the diameter of the intermediate stepped shafts is L303, and L303 is phi 190-⁰ _0.029The middle shaft is provided with middle chamfers on the outer diameters of two ends, the size of the middle chamfers is L306, L306 is 2 × 45 degrees mm, the outer diameter connecting position of the middle shaft is provided with a middle fillet, the size of the middle fillet is L307, L307 is R0.5, two ends of the middle disc are symmetrically provided with middle notches, the middle disc and the middle notches are coaxial, the diameter of the middle notches is L302, L302 is phi 170, the width of the middle notches is L312, L312 is 20mm, the middle disc is provided with a middle central through hole coaxially, the diameter of the middle central through hole is L301, L301 is phi 110mm, the width of the middle central through hole is L309, L is 20mm, a middle annular groove is arranged at the center of the outer wall of the middle disc, the width of the middle annular groove is L308, L308 is 30mm, the bottom diameter of the middle annular groove is L303, and L303 is phi 190 mm.

Preferably: the diameter of the second-stage wheel disc is L401, L401 is phi 310mm, the width of the second-stage wheel disc is L403, L403 is 60mm, second stepped shafts are symmetrically machined at the left end and the right end of the second-stage wheel disc, the second-stage wheel disc and the second stepped shafts are coaxial, the diameter of the second stepped shafts is L402, L402 is phi 260mm, the width of the second stepped shafts is L409, L409 is 20mm, second ports are machined on the coaxial lines of the second stepped shafts, the diameter of the second ports is L406, L406 is 190 phi_{+ 0} ^0.046mm, the width of the second port is L409, the L409 is 20mm, a second chamfer is machined on the outer side of the second port, the size of the second chamfer is L407, the L407 is 2 × 45, and a second central port is machined on the second-stage wheel disc coaxial lineThe diameter of the second center port is L405, L205 ═ phi 50mm, the width of the second center port is L408, L408 ═ 20mm, the second stepped shaft is processed with second tie rod holes, the second tie rod holes are through holes with the diameter of L404, L404 ═ 11mm, the number of the second tie rod holes is N, N second tie rod holes are circumferentially arrayed on the second stepped shaft with the axis of the second-stage wheel disc as the axis, N ═ 15, the diameter of the circumferential array of the second tie rod holes is L410, and L410 ═ phi 230 mm.

Preferably: the rear end shaft of the turbine comprises a conical ring body, a long shaft, a fixed disc and a ring body, wherein the fixed disc is arranged on the outer side of the end face of the conical ring body, the ring body is processed on the left end face of the fixed disc, the long shaft is arranged at the right end of the conical ring body, pull rod holes are uniformly distributed in the fixed disc, conical inner grooves are formed in the conical ring body, and the cone angle of each conical inner groove is 90 degrees;

the conical ring body, the long shaft and the ring body are integrally formed and processed, the total length of the conical ring body, the long shaft and the ring body is L501, and L501 is 635 mm; the thickness of the fixed disc is L502, the L502 is 10mm, the outer diameter of the fixed disc is L504, the L504 is phi 260mm, N pull rod holes are uniformly distributed in the fixed disc, the diameter of each pull rod hole is L511, the L511 is phi 11mm, the N middle pull rod holes are circumferentially arrayed on the fixed disc by taking the axis of the fixed disc as an axis, the N is 15, the diameter of the circumferential array of the pull rod holes is L513, and the L513 is phi 230 mm; the inner diameter of the torus is L506, L506 is phi 180mm, the outer diameter of the torus is L505, L505 is phi 190mm, the length of the torus is L503, and L503 is phi 5 mm; the distance from the cone vertex of the cone inner groove to the end face of the cone ring body is L510, and L510 is 90 mm; the diameter of the long shaft is L509, L509 is phi 40mm, the right side end part of the long shaft is chamfered into L508, and L508 is 0.7 multiplied by 45 degrees; the left side outline diameter of the conical ring body is L507, and L507 is phi 200 mm.

Preferably: the length of the short pull rod is L601, L601 is 52mm, the diameter of the short pull rod is L602, L602 is phi 10mm, threads are symmetrically machined at two ends of the short pull rod, the length of the threads is L603, L603 is 20mm, the threads are M10-6g, chamfers are machined at ends of the threads, the size of the chamfers at the end parts of the threads is L604, L604 is 0.5 multiplied by 45 degrees, the short pull rod sequentially penetrates through the second mounting hole, the first pull rod hole and the middle pull rod hole, the threads are connected with the nut, the short pull rod and the nut enable the short pull rod to connect, screw and fix the second mounting hole, the first pull rod hole and the middle pull rod hole, the short pull rod sequentially penetrates through the middle pull rod hole, the second pull rod hole and the pull rod hole in the fixed disc, the threads are connected with the nut, and the short pull rod and the nut enable the middle pull rod hole, the second pull rod hole and the pull rod hole in the fixed.

The invention has the following beneficial effects:

1. the invention has simple structure, low processing cost, convenient assembly, high safety and reliability under the working conditions of simulating high speed, heavy load and the like, and can better simulate and reflect the structural characteristics and the special dynamic characteristics of the turbine rotor of the heavy-duty gas turbine; the outer contour of the rotary table is more convenient to be matched with the rotor blade;

2. based on the structure of the invention, processing cracks can be manufactured at the thin-wall structure of the circular cone, the crack fault characteristics of the rotor are simulated, and a crack fault test database is obtained;

3. the invention is easy to install and disassemble, has reasonable structural design and is suitable for popularization and use.

Drawings

FIG. 1 is a front view of a modeled turbine rotor for use in a heavy duty gas turbine;

FIG. 2 is a front elevational view of the construction of the first stage wheel disc;

FIG. 3 is a structural side view of the first stage disk;

FIG. 4 is a front view of the structure of the intermediate tray;

FIG. 5 is a side view of the structure of the intermediate tray;

FIG. 6 is a front structural view of a second stage wheel disc;

FIG. 7 is a front elevational view of the construction of the turbine rear end shaft;

FIG. 8 is a structural side view of the turbine rear end shaft;

FIG. 9 is a schematic view of the construction of a short tie rod;

FIG. 10 is a schematic view of a heavy duty gas turbine modeled rotor structure;

FIG. 11 is a front elevational view of the construction of the turbine front end shaft;

FIG. 12 is a structural side view of a turbine front end shaft;

in the figure 1-turbine front end shaft, 11-first mounting disk, 111-first mounting hole, 12-second mounting disk, 121-second mounting hole, 13-front end shaft body, 14-boss ring, 15-cone frustum, 151-cone inner recess, 16-wheel disc positioning projection, 17-lightening hole, 18-wheel disc positioning hole, 2-first stage wheel disc, 21-first pull rod hole, 22-first port, 23-first center port, 24-first chamfer, 25-first step shaft, 3-middle disk, 31-middle notch, 32-middle center through hole, 33-middle stepped shaft, 34-middle ring recess, 35-middle pull rod hole, 36-middle chamfer, 37-middle fillet, 4-second stage wheel disc, 41-a second pull rod hole, 42-a second port, 43-a second central port, 44-a second chamfer, 45-a second step shaft, 5-a turbine rear end shaft, 51-a conical ring body, 52-a long shaft, 53-a fixed disc, 54-a circular ring body, 55-a conical inner groove, 6-a short pull rod and 61-a thread.

Detailed Description

In order that the objects, aspects and advantages of the invention will become more apparent, the invention will be described by way of example only, and in connection with the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.

The connection mentioned in the present invention is divided into a fixed connection and a detachable connection, the fixed connection (i.e. the non-detachable connection) includes but is not limited to a folding connection, a rivet connection, an adhesive connection, a welding connection, and other conventional fixed connection methods, the detachable connection includes but is not limited to a screw connection, a snap connection, a pin connection, a hinge connection, and other conventional detachment methods, when the specific connection method is not clearly defined, the function can be realized by always finding at least one connection method from the existing connection methods by default, and a person skilled in the art can select the connection method according to needs. For example: the fixed connection selects welding connection, and the detachable connection selects hinge connection.