Gas turbine rotor part mounting edge circumferential unloading groove structure

Abstract

The utility model discloses a gas turbine rotor component mounting edge circumferential unloading groove structure which comprises a rotor mounting edge, a plurality of bolt holes are formed in the outer wall of the rotor mounting edge in a surrounding mode at equal intervals in a penetrating mode, and a plurality of circumferential unloading grooves are formed in the inner wall of the rotor mounting edge in a surrounding mode at equal intervals in a penetrating mode. The inner walls of the two sides of the multiple circumferential unloading grooves are arranged in an arc shape, the inner bottom walls of the multiple circumferential unloading grooves are arranged in an arc shape, the diameters of the inner bottom walls of the multiple circumferential unloading grooves are smaller than the diameter of a bolt hole, force can be released, the inner bottom walls of the multiple circumferential unloading grooves are arranged in an arc shape, and the inner bottom walls of the multiple circumferential unloading grooves are arranged in an arc shape. The diameters of the inner bottom walls of the circumferential unloading grooves are smaller than the diameter of the bolt hole, so that the rotor mounting edge is prevented from being damaged due to stress, the stress of the rotor mounting edge can be reduced, the stress level of the hole edge is reduced, the reliability of the gas turbine rotor part is improved, and the weight of the mounting edge is reduced through the circumferential unloading grooves.

Description

Technical Field

[0001] The utility model relates to the technical field of rotor installation, in particular to a circumferential unloading groove structure on the installation side of a gas turbine rotor component. Background Art

[0002] The gas turbine rotor is the core component of a gas turbine. Its structure determines the performance and operational stability of the gas turbine. Based on different design and manufacturing requirements, gas turbine rotors are broadly classified into three types: drum, disc, and disc-drum.

[0003] As the load and speed of gas turbine rotor components increase, coupled with the influence of stress concentration effect, the stress level at the mounting edge hole of the gas turbine rotor becomes higher and higher. It is necessary to take necessary unloading methods to effectively unload this part to reduce the stress level at the mounting edge bolt hole. Therefore, it is necessary to propose a circumferential unloading groove structure for the mounting edge of gas turbine rotor components. Utility Model Content

[0004] The purpose of the utility model is to provide a circumferential unloading groove structure on the mounting edge of a gas turbine rotor component to solve the problems raised in the above-mentioned background technology.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a circumferential unloading groove structure for the mounting edge of a gas turbine rotor component, comprising a rotor mounting edge, wherein the outer wall of the rotor mounting edge is circumferentially and equidistantly penetrated with a plurality of bolt holes, and the inner wall of the rotor mounting edge is circumferentially and equidistantly penetrated with a plurality of circumferential unloading grooves, and the inner walls on both sides of the plurality of circumferential unloading grooves are both arranged in an arc shape.

[0006] Preferably, the inner bottom walls of several of the circumferential unloading grooves are all arranged in an arc shape, and the diameters of the inner bottom walls of several of the circumferential unloading grooves are all smaller than the diameter of the bolt hole.

[0007] Preferably, the lengths of the plurality of circumferential unloading grooves are all greater than the diameter of the bolt hole.

[0008] Preferably, the angles of the end faces on both sides of several of the circumferential unloading grooves are greater than degrees.

[0009] Compared with the prior art, the beneficial effects of the present invention are as follows: the inner walls of the circumferential unloading grooves are all arranged in an arc shape, which partially increases the thickness of the rotor mounting edge and increases the pressure resistance. When the rotor rotates, the inner walls on both sides of the circumferential unloading grooves are all in an arc shape, which can release the force and prevent the rotor mounting edge from being damaged by force. It can reduce the force on the rotor mounting edge, reduce the stress level of the hole edge, improve the reliability of the gas turbine rotor components, and at the same time reduce the weight of the mounting edge through the circumferential unloading grooves. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 This is a front view structural diagram of the utility model;

[0011] Figure 2 It is a structural diagram of the present utility model.

[0012] In the figure: 1. Rotor mounting edge; 2. Bolt holes; 3. Circumferential unloading groove. DETAILED DESCRIPTION

[0013] See also Figure 1-2 The utility model provides a technical solution: a circumferential unloading groove structure of a gas turbine rotor component mounting edge, comprising a rotor mounting edge 1, wherein the outer wall of the rotor mounting edge 1 is circumferentially and equidistantly penetrated with a plurality of bolt holes 2, and the inner wall of the rotor mounting edge 1 is circumferentially and equidistantly penetrated with a plurality of circumferential unloading grooves 3, and the inner walls on both sides of the plurality of circumferential unloading grooves 3 are both arranged in an arc shape.

[0014] Among them, the inner bottom walls of several circumferential unloading grooves 3 are all arranged in an arc shape, and the diameters of the inner bottom walls of several circumferential unloading grooves 3 are all smaller than the diameters of the bolt holes 2, which is convenient for increasing the thickness of the rotor mounting edge 1 and increasing the rigidity of the rotor mounting edge 1.

[0015] The lengths of the plurality of circumferential unloading grooves 3 are all greater than the diameter of the bolt hole 2 .

[0016] The angles of the end faces of the plurality of circumferential unloading grooves 3 are greater than 90 degrees.

[0017] Specifically, when the utility model is used, when the rotor rotates, the bolt is subjected to force. Since the circumferential unloading groove 3 is located in the middle of the bolt hole 2, the inner bottom wall of the circumferential unloading groove 3 is arc-shaped, which can increase the thickness of the rotor. At the same time, the arc shape increases the pressure resistance. The inner walls on both sides of the circumferential unloading groove 3 are both arranged in an arc shape, which can release the pressure when subjected to pressure, while increasing the pressure resistance.

Claims

1. A circumferential unloading groove structure of a gas turbine rotor component mounting edge, comprising a rotor mounting edge (1), characterized in that: The outer wall of the rotor mounting edge (1) is circumferentially and equidistantly penetrated with a plurality of bolt holes (2); the inner wall of the rotor mounting edge (1) is circumferentially and equidistantly penetrated with a plurality of circumferential unloading grooves (3); the inner walls on both sides of the plurality of circumferential unloading grooves (3) are arranged in an arc shape; the inner bottom walls of the plurality of circumferential unloading grooves (3) are arranged in an arc shape; and the diameters of the inner bottom walls of the plurality of circumferential unloading grooves (3) are all smaller than the diameters of the bolt holes (2).

2. A circumferential unloading groove structure for a gas turbine rotor component mounting edge according to claim 1, characterized in that: The lengths of the plurality of circumferential unloading grooves (3) are all greater than the diameter of the bolt hole (2).

3. The circumferential unloading groove structure of the gas turbine rotor component mounting edge according to claim 1, characterized in that: The angles of the end faces on both sides of a plurality of the circumferential unloading grooves (3) are greater than 90 degrees.

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