CN212027884U - Be applied to modular rotor turbine rear end axle of heavy gas turbine - Google Patents

Abstract

A rear end shaft of a modularized rotor turbine applied to a heavy-duty gas turbine belongs to the technical field of heavy-duty gas turbines. The utility model provides a be applied to the problem that heavy gas turbine rotor turbine rear end axle exists at present. The utility model discloses a cone ring body, major axis, fixed disk and tourus, the terminal surface outside of cone ring body is equipped with the fixed disk, and processing has the tourus on the left end face of fixed disk, and the right-hand member of cone ring body has the major axis, and evenly distributed has a plurality of round holes on the fixed disk, and the inside circular cone inner groovy that is equipped with of cone ring body, the cone angle of circular cone inner groovy is 90. The utility model discloses simple structure, the processing cost is low, convenient assembling tells in the simulation, fail safe nature is high under the operating mode such as heavy load, can simulate the structural feature of the heavy gas turbine pull rod rotor turbine rear end axle of reaction and its distinctive dynamics characteristic betterly.

Description

Be applied to modular rotor turbine rear end axle of heavy gas turbine

Technical Field

The utility model relates to a be applied to heavy gas turbine's modularization rotor turbine rear end axle belongs to heavy gas turbine technical field.

Background

The heavy gas turbine is the heat-power conversion type power generation equipment with the highest efficiency so far, is the core equipment in the field of power generation and driving, and intensively embodies the industrial level of a country due to the great difficulty in design and manufacture, and is also known as 'imperial pearl on the crown' in equipment manufacturing industry. The heavy gas turbine is clean and efficient power generation equipment, wherein a rotor is the most main core part, the heavy gas turbine rotor has various structural types and is mainly a pull rod type combined rotor, a rotor assembly comprises a plurality of rotor discs and a plurality of rotor blades, and the pull rod combined rotor provides pre-tightening force through a pull rod and is transmitted by the discs or friction surfaces.

These existing turbine rear shafts also suffer from the following disadvantages:

1. because the device works under the high-temperature, high-pressure, high-rotating-speed and heavy-load environments, cracks are easily generated locally in the using process;

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

In view of the foregoing, there is a need for a modular rotor turbine rear end shaft for use in a heavy duty gas turbine engine that solves the above problems.

SUMMERY OF THE UTILITY MODEL

The utility model provides a defect problem that present turbine rear end axle exists, to the not enough of prior art, the utility model discloses a "be applied to heavy gas turbine's modular rotor turbine rear end axle". A brief summary of the present invention is provided below in order to provide a basic understanding of some aspects of the present invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or critical elements of the invention or to delineate the scope of the invention.

The technical scheme of the utility model:

the utility model provides a be applied to heavy gas turbine's modularization rotor turbine rear end axle, includes the circular cone ring body, major axis, fixed disk and tourus, and the terminal surface outside of circular cone ring body is equipped with the fixed disk, and processing has the tourus on the left end face of fixed disk, and the right-hand member of circular cone ring body has the major axis, and evenly distributed has a plurality of round holes on the fixed disk, and the circular cone ring body is inside to be equipped with the circular cone inner groovy, and the cone angle of circular cone inner.

Preferably, the cone ring body, the long shaft and the ring body are integrally formed, the total length of the cone ring body, the long shaft and the ring body is L1, and L1 is 635 mm.

Preferably, the thickness of the fixed disk is L2, L2 is 10mm, the outer diameter of the fixed disk is L4, L4 is 260mm, 15 round holes are uniformly distributed on the fixed disk, the diameter of the round holes is L11, and L11 is 11 mm.

Preferably, the inner diameter of the torus is L6, L6 ═ phi 180mm, the outer diameter of the torus is L5, L5 ═ phi 190mm, the length of the torus is L3, and L3 is 5 mm.

Preferably, the distance from the cone vertex of the conical inner groove to the end face of the conical ring body is L10, and L10 is 90 mm.

Preferably, the diameter of the long shaft is L9, L9 is phi 40mm, the right end of the long shaft is chamfered at L8, and L8 is 0.7 × 45 °.

Preferably, the left side outline diameter of the conical ring body is L7, and L7 is 200 mm.

The utility model has the advantages that:

1. the utility model has the advantages of simple structure, the processing cost is low, convenient assembling, fail safe nature is high under operating modes such as simulation high speed, heavy load, structural feature and its distinctive dynamic characteristic of the heavy gas turbine pull rod rotor turbine rear end axle of simulation reaction that can be better.

2. Based on the utility model discloses a processing crackle can be made in ring centrum thin wall structure department to the structure, and the experimental database of crackle trouble is acquireed to simulation rotor crackle fault characteristic.

3. The utility model discloses easily installation and dismantlement, structural design is reasonable, is suitable for using widely.

Drawings

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

FIG. 2 is a front view of a modular rotor turbine rear end shaft mounting disk for a heavy duty gas turbine;

FIG. 3 is a general schematic view of a modeled rotor turbine rear end shaft for use in a heavy duty gas turbine;

FIG. 4 is a schematic illustration of the connection of the rear end shaft of a modular rotor turbine to the final disk for a heavy duty gas turbine.

In the figure: 1-a cone ring body, 2-a long shaft, 3-a fixed disc, 4-a ring body, 5-a cone inner groove and 6-a final stage wheel disc.

Detailed Description

In order to make the objects, solutions and advantages of the present invention more apparent, the present invention will be described with reference to the accompanying drawings. It should be understood that the description is intended to be exemplary, and not to limit the scope of the 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 first embodiment is as follows: the embodiment is described with reference to fig. 1 to 3, and the modularized rotor turbine rear end shaft applied to the heavy-duty gas turbine of the embodiment includes a conical ring body 1, a long shaft 2, a fixed disc 3 and a circular ring body 4, the fixed disc 3 is arranged outside the end surface of the conical ring body 1, the circular ring body 4 is processed on the left end surface of the fixed disc 3, the long shaft 2 is arranged at the right end of the conical ring body 1, a plurality of round holes are uniformly distributed on the fixed disc 3, a conical inner groove 5 is arranged inside the conical ring body 1, and the cone angle of the conical inner groove 5 is 90 °. The fixed disk 3 is used for the rear end axle to be connected with turbine last stage rim plate 6, and the tourus 4 is used for realizing the axial and radial location cooperation (as shown in figure 4) of rear end axle and last stage rim plate 6, and the cone ring body 1 is integrated with major axis 2 and is processed into one piece, and circular cone inner groovy 5 can guarantee that the turbine rotor reduces the weight of rotor when guaranteeing intensity, does benefit to the operation and the acceleration of product.

The second embodiment is as follows: the present embodiment is described with reference to fig. 1 to 3, and the rear end shaft of a modular rotor turbine applied to a heavy-duty gas turbine according to the present embodiment is formed by integrally molding a cone ring body, a long shaft, and a torus, wherein the total length of the cone ring body, the long shaft, and the torus is L1, and L1 is 635 mm.

The third concrete implementation mode: the embodiment is described with reference to fig. 1 to fig. 3, and the thickness of the fixed disk 3 is L2, L2 is 10mm, the outer diameter of the fixed disk 3 is L4, L4 is 260mm, 15 circular holes are uniformly distributed on the fixed disk 3, the diameter of the circular holes is L11, and L11 is 11 mm. So set up, the short bolt is connected with turbine last stage rim plate through the round hole on the fixed disk 3, and evenly distributed's round hole makes the rear end axle more firm fixed on turbine last stage rim plate.

The fourth concrete implementation mode: the present embodiment is described with reference to fig. 1 to 3, and the rear end shaft of a modeled rotor turbine applied to a heavy-duty gas turbine of the present embodiment has an inner diameter of the torus 4 of L6, L6 ═ phi 180mm, an outer diameter of the torus 4 of L5, L5 ═ phi 190mm, a length of the torus 4 of L3, and L3 ═ 5 mm.

The fifth concrete implementation mode: the present embodiment is described with reference to fig. 1 to 3, and the distance from the conical vertex of the conical inner groove 5 to the end face of the conical ring body 1 is L10, and L10 is 90mm in the modeled rotor turbine rear end shaft applied to a heavy-duty gas turbine of the present embodiment.

The sixth specific implementation mode: the present embodiment will be described with reference to fig. 1 to 3, and the diameter of the long shaft 2 is L9, L9 is phi 40mm, the right-side end chamfer of the long shaft 2 is L8, and L8 is 0.7 × 45 °, in the rear end shaft of a modeled rotor turbine applied to a heavy-duty gas turbine according to the present embodiment.

The seventh embodiment: the present embodiment is described with reference to fig. 1 to 3, and the left side outline diameter of the conical ring body 1 of the present embodiment is L7, and L7 is 200 mm. Based on the mechanism of the cone ring body 1, a processing crack can be manufactured at the thin-wall structure of the cone ring body 1, the crack fault characteristic of the rotor is simulated, and a crack fault test database is obtained.

It should be noted that, in the above embodiments, as long as the technical solutions can be aligned and combined without contradiction, those skilled in the art can exhaust all possibilities according to the mathematical knowledge of the alignment and combination, and therefore the present invention 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 present invention.

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 (7)

1. The utility model provides a be applied to heavy gas turbine's modularization rotor turbine rear end axle which characterized in that: including the cone ring body (1), major axis (2), fixed disk (3) and tourus (4), the terminal surface outside of cone ring body (1) is equipped with fixed disk (3), processing has tourus (4) on the left end face of fixed disk (3), and the right-hand member of cone ring body (1) has major axis (2), and evenly distributed has a plurality of round holes on fixed disk (3), and cone ring body (1) inside is equipped with circular cone inner groovy (5), and the cone angle of circular cone inner groovy (5) is 90.

2. The modeled rotor turbine aft shaft for a heavy duty gas turbine according to claim 1, wherein: the cone ring body (1), the long shaft (2) and the ring body (4) are integrally formed and processed, the total length of the cone ring body (1), the long shaft (2) and the ring body (4) is L1, and L1 is 635 mm.

3. The modeled rotor turbine aft shaft for a heavy duty gas turbine according to claim 1, wherein: the thickness of fixed disk (3) is L2, and L2 is 10mm, and the external diameter of fixed disk (3) is L4, and L4 is 260mm, and evenly distributed has 15 round holes on fixed disk (3), and the diameter of round hole is L11, and L11 is 11 mm.

4. The modeled rotor turbine aft shaft for a heavy duty gas turbine according to claim 1, wherein: the inner diameter of the torus (4) is L6, L6 is phi 180mm, the outer diameter of the torus (4) is L5, L5 is phi 190mm, the length of the torus (4) is L3, and L3 is phi 5 mm.

5. The modeled rotor turbine aft shaft for a heavy duty gas turbine according to claim 1, wherein: the distance from the cone vertex of the cone inner groove (5) to the end face of the cone ring body (1) is L10, and L10 is 90 mm.

6. The modeled rotor turbine aft shaft for a heavy duty gas turbine according to claim 1, wherein: the diameter of the long shaft (2) is L9, L9 is phi 40mm, the right end chamfer of the long shaft (2) is L8, and L8 is 0.7 multiplied by 45 degrees.

7. The modeled rotor turbine aft shaft for a heavy duty gas turbine according to claim 1, wherein: the left side outline diameter of the conical ring body (1) is L7, and L7 is 200mm phi.

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