CN111561356B - Be applied to heavy gas turbine's modularization turbine rotor - Google Patents
Be applied to heavy gas turbine's modularization turbine rotor Download PDFInfo
- Publication number
- CN111561356B CN111561356B CN202010430293.2A CN202010430293A CN111561356B CN 111561356 B CN111561356 B CN 111561356B CN 202010430293 A CN202010430293 A CN 202010430293A CN 111561356 B CN111561356 B CN 111561356B
- Authority
- CN
- China
- Prior art keywords
- phi
- pull rod
- disc
- diameter
- hole
- Prior art date
- Legal status (The legal status 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 status listed.)
- Active
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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model 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 well intermediate disk arrange in proper order, and turbine front end axle, first order rim plate and well intermediate disk pass through the short pull rod to be connected, and intermediate disk, second level rim plate and turbine rear end axle arrange in proper order, and intermediate disk, second level rim plate and turbine rear end axle pass through the short pull rod to be connected, and turbine front end axle, first order rim plate, intermediate disk, second level rim plate, turbine rear end axle and short pull rod are connected the back total length and are L1, L1 is equal to 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.
Description
Technical Field
The utility model 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, China is in a starting stage for the design and manufacture of the heavy-duty gas turbine rotor, a mature modeling model and theory do not exist in China, and a few developed countries are in monopoly on the technology.
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 utility model 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 utility model in order to provide a basic understanding of some aspects of the utility model. It should be understood that this summary is not an exhaustive overview of the utility model. 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 utility model 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 left 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 are connected through the short pull rod on right side, 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 200mm, 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 9, the phi 9 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 8 and L106, the phi 8 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 second 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 each second mounting hole 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 first order rim plate is L201, L201 is 360mm phi, the thickness of first order rim plate is L203, L203 is 60mm, first step shaft has been processed to the left and right sides both ends symmetry of first order rim plate, first order rim plate and first step shaft coaxial line, the diameter of first step shaft is L202, L202 is 260mm phi, the thickness of first step shaft is L209, L209 is 20mm, the coaxial line processing of first step shaft has first port, the diameter of first port is L206, L206 is phi
The thickness of the first port is L209, L209 is 20mm, a first chamfer is machined on the outer side of the first port, the size of the first chamfer is L207, L207 is 2 × 45 °, a first central port is machined coaxially on the first-stage wheel disc, the diameter of the first central port is L205, L205 is φ 50mm, the thickness of the first central port is L208, L208 is 20mm, a first pull rod hole is machined in the first stepped shaft, the first pull rod hole is a through hole 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 the axis, the N is 15, the diameter of the circumferential array of the first pull rod holes is L204, and L204 is φ 230 mm.
Preferably: the diameter of the middle disc is L304, L304 is phi 260mm, the thickness of the middle disc is L305, L305 is 60mm, middle pull rod holes are machined in the two ends of the middle disc, the number of the middle pull rod holes is N, the middle pull rod holes are through holes, the N middle pull rod holes are circumferentially arrayed on the middle disc by taking the axis of the middle disc as an axis, N is 15, the diameter of the circumferential array of the middle pull rod holes is L313, L313 is phi 230mm, middle stepped shafts are symmetrically machined in the two ends of the middle disc, the middle disc and the middle stepped shafts are coaxial, the thickness of the middle stepped shafts is L310, L310 is 5mm, and the diameter of the middle stepped shafts is L303,
both ends of the intermediate stepped shaftThe outer diameter of the middle chamfer is L306, the size of the middle chamfer is 2 multiplied by 45 mm, the outer diameter joint of the middle stepped shaft is provided with a middle fillet, the size of the middle fillet is L307, the size of the L307 is R0.5, middle notches are symmetrically arranged at two ends of the middle disk, the middle disk and the middle notches are coaxial, the diameter of the middle notches is L302, the L302 is phi 170, the thickness of the middle notches is L312, the L312 is 20mm, the middle disk is coaxially provided with a middle central through hole, the diameter of the middle central through hole is L301, the L301 is 110 phi, the thickness of the middle central through hole is L309, the L309 is 20mm, a middle annular groove is arranged at the center of the outer wall of the middle disk, the thickness of the middle annular groove is L308, the L308 is 30mm, the bottom diameter of the middle annular groove is L303, the L303 is phi 190mm, and the middle annular groove is positioned between the middle pull rod holes at two ends.
Preferably: the diameter of the second-stage wheel disc is L401, L401 is phi 310mm, the thickness 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 thickness of the second stepped shafts is L409, L409 is phi 20mm, a second port is machined on the coaxial lines of the second stepped shafts, and the diameter of the second port is L406,
the thickness of the second port is L409, L409 is 20mm, a second chamfer is machined on the outer side of the second port, the size of the second chamfer is L407, L407 is 2 × 45 °, a second central port is machined coaxially on the second-stage wheel disc, the diameter of the second central port is L405, L405 is φ 50mm, the thickness of the second central port is L408, L408 is 20mm, a second pull rod hole is machined in the second stepped shaft, the second pull rod hole is a through hole with the diameter of L404, L404 is 11mm, the number of the second pull rod holes is N, the N second pull rod holes are circumferentially arrayed on the second stepped shaft by taking the axis of the second-stage wheel disc as the axis, N is 15, the circumferential array diameter of the second pull rod holes is L410, and L410 is φ 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 disk is L502, the L502 is 10mm, the outer diameter of the fixed disk is L504, the L504 is phi 260mm, N pull rod holes are uniformly distributed in the fixed disk, the diameter of each pull rod hole is L511, the L511 is phi 11mm, the N pull rod holes are circumferentially arrayed on the fixed disk by taking the axis of the fixed disk 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 chamfers at ends of the threads are L604, L604 is 0.5 multiplied by 45 degrees, the left short pull rod sequentially penetrates through the second mounting hole, the first pull rod hole and the left middle pull rod hole, the threads are connected with the nut, the left short pull rod and the nut connect and screw the second mounting hole, the first pull rod hole and the left middle pull rod hole, the right short pull rod sequentially penetrates through the right middle pull rod hole, the second pull rod hole and the pull rod hole in the fixed disk, the threads are connected with the nut, and the right short pull rod and the nut connect and screw the right middle pull rod hole, the second pull rod hole and the pull rod hole in the fixed disk.
The utility model has the following beneficial effects:
1. the utility model has simple structure, low processing cost, convenient assembly and high safety and reliability under the working conditions of 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 utility model, 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 utility model 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 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 utility model will become more apparent, the utility model 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.
The first specific implementation way is as follows: the embodiment is described with reference to fig. 1 to 12, and the modeled turbine rotor applied to a heavy-duty gas turbine of the embodiment includes a turbine front end shaft 1, a first stage wheel disc 2, an intermediate disc 3, a second stage wheel disc 4, a turbine rear end shaft 5 and a short pull rod 6, wherein the turbine front end shaft 1, the first stage wheel disc 2 and the intermediate disc 3 are sequentially arranged, the turbine front end shaft 1, the first stage wheel disc 2 and the intermediate disc 3 are connected by the short pull rod 6 on the left side, the intermediate disc 3, the second stage wheel disc 4 and the turbine rear end shaft 5 are sequentially arranged, the intermediate disc 3, the second stage wheel disc 4 and the turbine rear end shaft 5 are connected by the short pull rod 6 on the right side, the total length of the connected turbine front end shaft 1, the first stage wheel disc 2, the intermediate disc 3, the second stage wheel disc 4, the turbine rear end shaft 5 and the short pull rod 6 is L1, L1 is 995mm, the structure is simple, the processing cost is low, the assembly is convenient, the safety and reliability are high under the working conditions of simulating high speed, heavy load and the like, and the structural characteristics and the specific dynamic characteristics of the heavy-duty gas turbine rotor can be well simulated and reflected.
The second embodiment is as follows: referring to fig. 1, 10, 11 and 12, the present embodiment, a modeled turbine rotor applied to a heavy duty gas turbine, the turbine front end shaft 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, 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 in the cone frustum 15, a wheel disc positioning bulge 16 is arranged at the bottom of the conical inner groove 151, a plurality of round holes are uniformly distributed on the first mounting disc 11 and the second mounting disc 12 respectively, the first mounting disc 11 is connected and mounted with a turbine rear end shaft, and the second mounting disc 12 is connected and mounted with the first-stage wheel disc 2;
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 124, 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, phi 3 is 11mm, the first mounting holes 111 are used for being connected with a rear end shaft of a turbine through bolts, and the rear end shaft positioning groove realizes axial positioning with the rear end shaft of the turbine;
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, phi 5 is 80mm, and the lightening hole 17 enables the front end shaft body 13 to achieve lightening while ensuring strength;
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 200mm, 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 end face at the bottom of the conical inner groove 151, the thickness of the wheel disc positioning bulge 16 is L105, the L105 is 40.5mm, the outer diameter of the wheel disc positioning bulge 16 is phi 9, the phi 9 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 8 and L106, the phi 8 is 50mm, the L106 is 28mm, and the wheel disc positioning hole 18 is used for realizing the axial positioning of the connecting center of the first-stage wheel disc 2;
the thickness of the second mounting disc 12 is L107, L107 is 10mm, the outer diameter of the first mounting disc 11 is phi 10, phi 10 is 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 180mm, the conical angle is 90 °, 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, phi 12 is 11mm, and the second mounting holes 121 are fixedly mounted with the first-stage wheel disc 2 through tie rods;
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, phi 13 is 190mm, and the boss ring 14 is used for realizing axial and radial positioning with the first-stage wheel disc 2;
the first mounting disc 11, the second mounting disc 12, the front end shaft body 13, the boss ring 14, the truncated cone 15 and the wheel disc positioning bulge 16 are integrally formed, the total length of the first mounting disc 11, the second mounting disc 12, the front end shaft body 13, the boss ring 14, the truncated cone 15 and the wheel disc positioning bulge 16 is L109, and L109 is 213 mm.
The third concrete implementation mode: referring to fig. 1 to 3, the present embodiment is described, in which a modeled turbine rotor applied to a heavy-duty gas turbine has a first-stage disk 2 having a diameter L201, where L201 is 360mm, a first-stage disk 2 having a thickness L203, where L203 is 60mm, first stepped shafts 25 are symmetrically formed at left and right ends of the first-stage disk 2,the first-stage wheel disc 2 is coaxial with the first stepped shaft 25, the diameter of the first stepped shaft 25 is L202, L202 is phi 260mm, the thickness of the first stepped shaft 25 is L209, L209 is 20mm, a first port 22 is machined on the coaxial line of the first stepped shaft 25, the diameter of the first port 22 is L206,
the thickness 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 °, the first stage disk 2 is coaxially machined with a first central port 23, the diameter of the first central port 23 is L205, L205 is phi 50mm, the thickness of the first central port 23 is L208, L208 is 20mm, a first tie rod hole 21 is machined on the first stepped shaft 25, the first tie rod hole 21 is a through hole with the diameter of L210, L210 is 11mm, the number of the first tie rod holes 21 is N, N first tie rod holes 21 are circumferentially arrayed on the first stepped shaft 25 by taking the axis of the first stage disk 2 as the axis, N is 15, the circumferential array diameter of the first tie rod hole 21 is L204, and L204 is phi 230mm, and based on the actual distribution situation of the disk and the blade structure, the disk and the outer profile size of the first stage disk can be modeled differently.
The fourth concrete implementation mode: referring to fig. 1, 4 and 5, the modeled turbine rotor applied to a heavy-duty gas turbine according to the present embodiment is described, where the diameter of the intermediate disk 3 is L304, L304 is phi 260mm, the thickness of the intermediate disk 3 is L305, L305 is 60mm, the intermediate disk 3 has intermediate tie rod holes 35 formed at both ends, the number of the intermediate tie rod holes 35 is N, the intermediate tie rod holes 35 are through holes, N intermediate tie rod holes 35 are circumferentially arrayed on the intermediate disk 3 with the axis of the intermediate disk 3 as the axis, N is 15, the circumferential array diameter of the intermediate tie rod holes 35 is L313, L313 is phi 230mm, the intermediate stepped shafts 33 are symmetrically formed at both ends of the intermediate disk 3, the intermediate disk 3 is coaxial with the intermediate stepped shafts 33, the thickness of the intermediate stepped shafts 33 is L310, L310 is phi 5mm, the diameter of the intermediate stepped shafts 33 is L303,
the outer diameters of the two ends of the intermediate stepped shaft 33 are provided with intermediate chamfers 36, the size of the intermediate chamfers 36 is L306, and L306 is equal to L3062 × 45 °, an intermediate fillet 37 is formed at the connection of the outer diameters of the intermediate stepped shafts 33, the size of the intermediate fillet 37 is L307, L307 is R0.5, intermediate recesses 31 are symmetrically formed at both ends of the intermediate disc 3, the intermediate disc 3 and the intermediate recesses 31 are coaxial, the diameter of the intermediate recess 31 is L302, L302 is phi 170mm, the thickness of the intermediate recess 31 is L312, L312 is 20mm, the intermediate disc 3 is coaxially formed with an intermediate central through hole 32, the diameter of the intermediate central through hole 32 is L301, L301 is 110mm, the thickness of the intermediate central through hole 32 is L309 phi, L309 is 20mm, an intermediate annular groove 34 is formed at the center of the outer wall of the intermediate disc 3, the thickness of the intermediate annular groove 34 is L308, L308 is 30mm, the bottom diameter of the intermediate annular groove 34 is L303, L303 is phi 190mm, and the intermediate annular groove 34 is located between the intermediate tie rod holes 35 at both ends.
The fifth concrete implementation mode is as follows: the present embodiment is described with reference to fig. 1 and 6, wherein the diameter of the second-stage disk 4 is L401, L401 is 310mm, the thickness of the second-stage disk 4 is L403, L403 is 60mm, second step shafts 45 are symmetrically machined at the left and right ends of the second-stage disk 4, the second-stage disk 4 and the second step shafts 45 are coaxial, the diameter of the second step shafts 45 is L402, L402 is 260mm, the thickness of the second step shafts 45 is L409, L409 is 20mm, second ports 42 are machined on the coaxial lines of the second step shafts 45, the diameter of the second ports 42 is L406,
the thickness of the second port 42 is L409, L409 is 20mm, a second chamfer 44 is machined on the outer side of the second port 42, the size of the second chamfer 44 is L407, L407 is 2 × 45 °, the second stage wheel 4 is coaxially machined with a second central port 43, the diameter of the second central port 43 is L405, L205 is phi 50mm, the thickness of the second central port 43 is L408, L408 is 20mm, a second pull rod hole 41 is machined on the second stage axle 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 stage axle 45 by taking the axis of the second stage wheel 4 as an axis, N is 15, the diameter of the circumferential array of the second pull rod holes 41 is L410, L410 is phi 230mm, and the third stage wheel 4 is phi 230mmThe primary wheel disc 2, the intermediate disc 3 and the secondary wheel disc 4 are in clearance fit by H7/H6 to realize radial positioning fit; the first-stage wheel disc 2, the intermediate disc 3, the second-stage wheel disc 4 are connected through the short pull rod 6 in a pre-tightening mode, a multi-stage turbine rotor structure can be formed through the connection combination mode, and different outer contour sizes of the first-stage wheel disc 2, the intermediate disc 3 and the second-stage wheel disc 4 can be modeled based on the actual distribution conditions of the rotor wheel disc and the blade structure of the combustion engine.
The sixth specific implementation mode: the present embodiment is described with reference to fig. 1, 7, and 8, and the turbine rear end shaft 5 of the present embodiment includes a conical ring body 51, a long shaft 52, a fixed disk 53, and a circular ring body 54, the fixed disk 53 is disposed on the outer side of the end surface of the conical ring body 51, the circular ring body 54 is processed on the left end surface of the fixed disk 53, the long shaft 52 is disposed at the right end of the conical ring body 51, a plurality of circular holes are uniformly distributed on the fixed disk 53, a conical inner groove 55 is disposed inside the conical ring body 51, and the cone angle of the conical inner groove 55 is 90 °. The fixed disc 53 is used for connecting the rear end shaft with the secondary wheel disc 4, the circular ring body 54 is used for realizing the axial and radial positioning matching of the rear end shaft and the secondary wheel disc 4, the conical ring body 51 and the long shaft 52 are integrally processed and formed, and the conical inner groove 55 can ensure that the weight of the rotor is reduced while the strength of the turbine rotor is ensured, thereby being beneficial to the operation and the speed increase of products;
the conical ring body 51, the long shaft 52 and the circular ring body 54 are integrally formed and processed, 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 disk 53 is L502, the L502 is 10mm, the outer diameter of the fixed disk 53 is L504, the L504 is 260mm, N tie rod holes are uniformly distributed on the fixed disk 53, the diameter of each tie rod hole is L511, the L511 is 11mm, the N tie rod holes are circumferentially arrayed on the fixed disk 53 by taking the axis of the fixed disk 53 as an axis, and the N is 15, so that the short tie rods 6 pass through the tie rod holes on the fixed disk 53 to be connected with the secondary wheel disk 4, and the tie rod holes which are uniformly distributed enable the turbine rear end shaft 5 to be more firmly fixed on the secondary wheel disk; the diameter of the circumferential array of the pull rod holes is L513, and L513 is 230 mm; the inner diameter of the torus 54 is L506, L506 is 180mm, the outer diameter of the torus 54 is L505, L505 is 190mm, the length of the torus 54 is L503, and L503 is 5 mm; the distance from the conical vertex of the conical inner groove 55 to the end face of the conical 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 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 200mm, based on the mechanism of the conical ring body 51, a processing crack can be manufactured at the thin-wall structure of the conical ring body 51, the crack fault characteristic of a rotor can be simulated, and a crack fault test database can be obtained.
The seventh concrete implementation mode: the present embodiment is described with reference to fig. 1 to 10, and the modeled turbine rotor applied to a heavy-duty gas turbine of the present embodiment is characterized in that the length of the short tie rod 6 is L601, L601 is 52mm, the diameter of the short tie rod 6 is L602, L602 is phi 10mm, threads 61 are symmetrically machined at both ends of the short tie rod 6, the length of the threads 61 is L603, L603 is 20mm, the threads 61 are M10-6g, chamfers are machined at the ends of the threads 61, the size of the chamfer at the end of the thread 61 is L604, L604 is 0.5 × 45 °, the left short tie rod 6 sequentially passes through the second mounting hole 121, the first tie rod hole 21 and the left middle tie rod hole 35, the threads 61 are connected with a nut, the left short tie rod 6 and the nut connect and fix the short tie rod 6 with the second mounting hole 121, the first tie rod hole 21 and the left middle tie rod hole 35, and the right short tie rod 6 sequentially passes through the right middle tie rod hole 35, The second pull rod hole 41 and the pull rod hole in the fixed disc 53 are connected through threads 61 and nuts, the middle pull rod hole 35 at the right end, the second pull rod hole 41 and the pull rod hole in the fixed disc 53 are connected and screwed fixedly through the short pull rod 6 and the nuts on the right side, and the short pull rod 6 is in clearance fit with the turbine front-end shaft 1, the first-stage wheel disc 2, the middle disc 3, the second-stage wheel disc 4 and the turbine rear-end shaft 5.
It should be noted that, in the above embodiments, as long as the technical solutions can be aligned and combined without contradiction, a person skilled in the art can exhaust all possibilities according to the mathematical knowledge of the alignment and combination, and therefore the utility model does not describe the technical solutions after alignment and combination one by one, but it should be understood that the technical solutions after alignment and combination have been disclosed by the utility model.
This embodiment is only illustrative of the patent and does not limit the scope of protection thereof, and those skilled in the art can make modifications to its part without departing from the spirit of the patent.
Claims (6)
1. A modular turbine rotor for a heavy duty gas turbine engine, comprising: the front end shaft (1), the first-stage wheel disc (2), the middle disc (3), the second-stage wheel disc (4), the rear end shaft (5) of the turbine and the short pull rod (6) are sequentially arranged, the front end shaft (1), the first-stage wheel disc (2) and the middle disc (3) of the turbine are connected through the left short pull rod (6), the middle disc (3), the second-stage wheel disc (4) and the rear end shaft (5) of the turbine are sequentially arranged, the middle disc (3), the second-stage wheel disc (4) and the rear end shaft (5) of the turbine are connected through the right short pull rod (6), the front end shaft (1), the first-stage wheel disc (2), the middle disc (3), the second-stage wheel disc (4), the rear end shaft (5) of the turbine and the short pull rod (6) of the turbine are connected, and then the total length is L1, wherein L1 is 995 mm;
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 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, the N 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 the circumferential array of the pull rod holes 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.
2. A modular turbine rotor for a heavy duty gas turbine according to claim 1, wherein: 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 200mm, 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 L105, the L105 is 40.5mm, the outer diameter of the wheel disc positioning bulge (16) is phi 9, the phi 9 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 8 and L106, the phi 8 is 50mm, and the L106 is 28 mm;
the thickness of the second mounting disc (12) is L107, L107 is equal to 10mm, the outer diameter of the second mounting disc (12) 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 thickness 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 thickness 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 thickness of the first port (22) is L209, L209 is 20mm, and the outside of the first port (22) is addedThe first step wheel disc structure is characterized in that a first chamfer (24) is formed, the size of the first chamfer (24) is L207, L207 is 2 multiplied by 45 degrees, a first central port (23) is coaxially formed in the first step wheel disc (2), the diameter of the first central port (23) is L205, L205 is phi 50mm, the thickness of the first central port (23) is L208, L208 is 20mm, a first pull rod hole (21) is formed in the first step 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, the N first pull rod holes (21) are circumferentially arrayed on the first step shaft (25) by taking the axis of the first step wheel disc (2) as an axis, N is 15, the diameter of the first pull rod hole (21) is L204, and L204 is phi 230 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 thickness of the intermediate disc (3) is L305, L305 is 60mm, intermediate pull rod holes (35) are machined in the two ends of the intermediate disc (3), the number of the intermediate pull rod holes (35) is N, the intermediate pull rod holes (35) are through holes, the N intermediate pull rod holes (35) are circumferentially arrayed on the intermediate disc (3) by taking the axis of the intermediate disc (3) as an axis, N is 15, the diameter of the circumferential array of the intermediate pull rod holes (35) is L313, L313 is phi 230mm, intermediate stepped shafts (33) are symmetrically machined in the two ends of the intermediate disc (3), the intermediate disc (3) and the intermediate stepped shafts (33) are coaxial, the thickness of the intermediate stepped shafts (33) is L310, L310 is phi 5mm, and the diameter of the intermediate stepped shafts (33) is L303,
the outer diameters of two ends of an intermediate stepped shaft (33) are provided with intermediate chamfers (36), the size of the intermediate chamfers (36) is L306, L306 is 2 multiplied by 45 degrees, intermediate fillets (37) are arranged at the outer diameter connecting positions of the intermediate stepped shaft (33), the size of the intermediate fillets (37) is L307, L307 is R0.5, intermediate notches (31) are symmetrically arranged at two ends of an intermediate disk (3), the intermediate disk (3) is coaxial with the intermediate notches (31), the diameter of the intermediate notches (31) is L302, L302 is 170mm, the thickness of the intermediate notches (31) is L312 phi, L312 is 20mm, the intermediate disk (3) is coaxially provided with an intermediate central through hole (32), the diameter of the intermediate central through hole (32) is L301, L301 is 110mm, and the intermediate central through hole (32) is L301, L301 is phi 110mmThe thickness of the middle central through hole (32) is L309, L309 is 20mm, a middle annular groove (34) is machined in the center of the outer wall of the middle disc (3), the thickness of the middle annular groove (34) is L308, L308 is 30mm, the diameter of the bottom of the middle annular groove (34) is L303, L303 is phi 190mm, and the middle annular groove (34) is located between the middle pull rod holes (35) at the two ends.
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 thickness 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 thickness 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 thickness of the second port (42) is L409, the L409 is 20mm, a second chamfer (44) is machined on the outer side of the second port (42), the size of the second chamfer (44) is L407, the L407 is 2 × 45 degrees, a second central port (43) is machined on the second-stage wheel disc (4) coaxially, the diameter of the second central port (43) is L405, the L405 is phi 50mm, the thickness of the second central port (43) is L408, the L408 is 20mm, second pull rod holes (41) are machined in the second stepped shaft (45), the second pull rod holes (41) are through holes with the diameter of L404, the L404 is 11mm, the number of the second pull rod holes (41) is N, the N second pull rod holes (41) are distributed on the second stepped shaft (45) in an array with the axis of the second-stage wheel disc (4) as a circle center, the N is 15, the array of the second pull rod holes (41) is L410 mm, and the diameter of L410 mm is L410 mm.
6. A modular turbine rotor for a heavy duty gas turbine according to claim 5, 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 the threads (61) is L603, L603 is 20mm, the threads (61) are M10-6g, chamfers are machined at the ends of the threads (61), the chamfers at the ends of the threads (61) are L604, L604 is 0.5 multiplied by 45 degrees, the left short pull rod (6) sequentially penetrates through the second mounting hole (121), the first pull rod hole (21) and the left middle pull rod hole (35), the threads (61) are connected with a nut, the left short pull rod (6) and the nut connect and screw the second mounting hole (121), the first pull rod hole (21) and the left middle pull rod hole (35) tightly, the right short pull rod (6) sequentially penetrates through the right 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) on the right side and the nut connect, screw and fix the middle pull rod hole (35) on the right end, the second pull rod hole (41) and the pull rod hole on the fixed disc (53).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010430293.2A CN111561356B (en) | 2020-05-20 | 2020-05-20 | Be applied to heavy gas turbine's modularization turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010430293.2A CN111561356B (en) | 2020-05-20 | 2020-05-20 | Be applied to heavy gas turbine's modularization turbine rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111561356A CN111561356A (en) | 2020-08-21 |
| CN111561356B true CN111561356B (en) | 2022-06-14 |
Family
ID=72073464
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010430293.2A Active CN111561356B (en) | 2020-05-20 | 2020-05-20 | Be applied to heavy gas turbine's modularization turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111561356B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112432793A (en) * | 2020-11-23 | 2021-03-02 | 东方电气集团东方汽轮机有限公司 | Gas turbine wheel disc air extraction test piece and modeling test parameter design method |
| CN112444398A (en) * | 2020-11-23 | 2021-03-05 | 东方电气集团东方汽轮机有限公司 | Gas turbine rotor cold air conveying test piece and test parameter design method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1349170A (en) * | 1970-07-09 | 1974-03-27 | Kraftwerk Union Ag | Rotor for a gas turbine engine |
| CN103016080A (en) * | 2012-12-31 | 2013-04-03 | 北京全四维动力科技有限公司 | Multistage steam turbine adopting wheel disc pull rod structure |
| CN104420887B (en) * | 2013-08-30 | 2016-06-15 | 哈尔滨汽轮机厂有限责任公司 | A kind of turbine of gas turbine |
| EP2933432A1 (en) * | 2014-04-15 | 2015-10-21 | Siemens Aktiengesellschaft | Rotor with axially secured support ring |
-
2020
- 2020-05-20 CN CN202010430293.2A patent/CN111561356B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN111561356A (en) | 2020-08-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111561356B (en) | Be applied to heavy gas turbine's modularization turbine rotor | |
| CN110332018B (en) | High-compactness closed circulation runoff turbine power generation system rotor | |
| CN107462966A (en) | A kind of flexible support structure for miniature remote sensing load speculum | |
| CN111207609A (en) | Bionic-based heat exchanger core body with compact honeycomb-like structure and heat exchanger | |
| CN107269316A (en) | A kind of disc of conical profile structure of gas turbine central draw bar type rotor | |
| CN211202406U (en) | Compressor wheel disc applied to modeled pull rod rotor of heavy gas turbine | |
| CN211740628U (en) | Wheel disc test piece applied to pull rod rotor | |
| CN110821883A (en) | Modularized compressor rotor applied to heavy gas turbine | |
| CN207723500U (en) | Lathe handle of a knife conversion equipment | |
| CN203037525U (en) | Clamping tool for thin walled tube fatigue test | |
| CN109489950B (en) | Connecting structure for fatigue test of high-pressure compressor disk of engine | |
| CN209724782U (en) | Gas turbine and its fan spindle bearing support construction | |
| CN212428955U (en) | Be applied to modeling rotor turbine front end axle of heavy gas turbine | |
| CN212027884U (en) | Be applied to modular rotor turbine rear end axle of heavy gas turbine | |
| CN103343704A (en) | Open-type integrated nozzle block structure and machining method | |
| CN211174742U (en) | Compressor rear end shaft of modularized pull rod rotor | |
| CN102777497B (en) | Floating bearing and turbocharger comprising same | |
| CN215334031U (en) | Switching dish convenient to dismouting | |
| CN209444961U (en) | A kind of buffer compensator | |
| CN108678813B (en) | Pull rod rotor with self-locking nut device | |
| CN116146290A (en) | Rotor shafting structure of large turbine expander | |
| CN211939974U (en) | Three-piece combined type planet frame machining clamp | |
| CN202991904U (en) | Coupling for emergency use | |
| CN113530991A (en) | Structure for shortening butt joint axial size of transfer case | |
| RU2487272C1 (en) | Rotary pump with gap-free attachment of impeller and end seals to rotor shaft and method of improving pump performances |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |