CN211520384U

CN211520384U - Gas turbine blade bearing seat

Info

Publication number: CN211520384U
Application number: CN201921790753.1U
Authority: CN
Inventors: 叶计拉
Original assignee: Mitsubishi Heavy Industries Dongfang Gas Turbine Guangzhou Co Ltd
Current assignee: Mitsubishi Heavy Industries Dongfang Gas Turbine Guangzhou Co Ltd
Priority date: 2019-10-23
Filing date: 2019-10-23
Publication date: 2020-09-18
Anticipated expiration: 2029-10-23

Abstract

The utility model discloses a gas turbine blade bearing seat, which comprises a base arranged in a plate shape, wherein a first accommodating cavity is arranged on the upper end surface of the base, the first accommodating cavity is a first groove, the first groove is arranged along the length direction of the base, and the first accommodating cavity is used for placing a moving blade; the upper end surface of the base is also provided with a second accommodating cavity, the second accommodating cavity is used for placing a stationary blade, and the second accommodating cavity takes the axis of the first groove as a datum line and is intersected with the first accommodating cavity; or the first and second receiving chambers are separated from each other on the base; the gas turbine blade bearing seat has the advantages of reasonable structure, high universality and simplicity and convenience in use.

Description

Gas turbine blade bearing seat

Technical Field

The utility model belongs to the technical field of gas turbine equipment, concretely relates to a bear seat for placing gas turbine or steam turbine blade.

Background

The Gas Turbine (Gas Turbine) is a rotary power machine which takes continuous flowing Gas as working medium and converts heat energy into mechanical work, and the main structure of the Gas Turbine is composed of a Turbine or a power Turbine, a Gas compressor and a combustion chamber. The working principle is as follows: the vane compressor absorbs air from the outside, compresses the air and sends the air into the combustion chamber, and simultaneously fuel (gas or liquid fuel) is also sprayed into the combustion chamber to be mixed with high-temperature compressed air and combusted. The generated high-temperature high-pressure flue gas enters a gas turbine to be expanded to push power blades to rotate at a high speed, and exhaust gas is discharged into the atmosphere or is reused. The principle of the steam turbine is similar to that of the gas turbine, and the main difference is that the steam turbine does not have a combustion chamber and directly uses high-pressure steam as a driving energy source. The gas turbine has the advantages of high efficiency, large power, small volume, investment saving, low operation cost, long service life and the like, so the gas turbine is mainly used for power generation, traffic and industrial power. One of the core components of a gas turbine is a plurality of moving blades mounted on a main shaft and forming the rotor of a particular multi-stage impeller assembly, and stationary blades mounted in a casing and cooperating with the rotor of moving blades to form the compressor or turbine of the gas turbine. Because the rotating speed of the gas turbine usually reaches tens of thousands of revolutions per minute, and the moving and static blades usually bear thousands of high temperatures, the manufacturing of the moving and static blades of the gas turbine is very precise and complicated; need place on solitary bear the seat so that carry out the interim fixed transportation to the blade after the blade preparation is accomplished, prevent that the blade from taking place to collide with and leading to the blade to produce the damage even scrap in the transportation. However, the blade bearing seats in the prior art are single in function and low in universality, that is, the stationary blades and the moving blades need to be respectively placed on the respective bearing seats by the separate stationary blade bearing seats or moving blade bearing seats, and the moving blades and the stationary blades often have multiple specifications, so that certain inconvenience is brought to the placement and the transfer of the blades by separately providing the different bearing seats.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model aims at providing a gas turbine blade bears seat rational in infrastructure, commonality are high, simple to use is convenient.

In order to solve the technical problem, the utility model discloses the technical scheme who uses is:

a gas turbine blade bearing seat comprises a platy base, wherein a first accommodating cavity is formed in the upper end face of the base, the first accommodating cavity is a first groove, the first groove is formed in the length direction of the base, and the first accommodating cavity is used for accommodating a moving blade; the upper end surface of the base is also provided with a second accommodating cavity, the second accommodating cavity is used for placing a stationary blade, and the second accommodating cavity takes the axis of the first groove as a datum line and is intersected with the first accommodating cavity;

or the first receiving chamber and the second receiving chamber are separated from each other on the base.

Preferably, the second accommodating cavity comprises second grooves respectively located at two ends of the first groove, and the second grooves are mutually centrosymmetric.

Preferably, the second accommodating cavity further comprises third grooves respectively located at two ends of the first groove, and the third grooves are mutually centrosymmetric.

Preferably, the third groove and the second groove are overlapped with each other; or the third groove and the second groove are separated from each other.

Preferably, the two sides of the first groove are respectively provided with a fourth groove, the fourth grooves are mutually centrosymmetric, and the fourth grooves are positioned between the second grooves or the third grooves.

Preferably, the second groove and the third groove are arranged obliquely with respect to the first groove.

Preferably, the fourth grooves are all parallel to the first grooves.

Preferably, the first groove is in an inverted trapezoid shape, and the depth of the first groove is greater than the depth of the second groove, the depth of the third groove and the depth of the fourth groove.

Preferably, the length of the second groove is greater than the length of the third groove.

The beneficial effects of the utility model are mainly embodied in that: because the first accommodating cavity and the second accommodating cavity are arranged on the base, moving blades or static blades of a gas turbine or a steam turbine can be placed on the base, namely, compared with the prior art, when the moving blades and the static blades are placed and transferred, the bearing seat does not need to be distinguished to be suitable for the moving blades or the static blades, so that the universality and the convenience of the bearing seat during use are improved; particularly, when the first accommodating cavity and the second accommodating cavity are intersected or overlapped with each other, the volume of the base can be further reduced, namely, the production cost of the bearing seat is reduced.

Drawings

The foregoing and other objects, features and advantages of the invention will be apparent from the following more particular description of preferred embodiments of the invention, as illustrated in the accompanying drawings. Like reference numerals refer to like parts throughout the drawings, and the drawings are not intended to be drawn to scale in actual dimensions, emphasis instead being placed upon illustrating the principles of the invention.

FIG. 1 is a schematic top view of a gas turbine blade carrier according to the present invention;

fig. 2 is a schematic perspective view of a gas turbine blade bearing seat according to the present invention.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments so that those skilled in the art can better understand the present invention and can implement the present invention, but the illustrated embodiments are not intended to limit the present invention, and in the present embodiments, it is understood that the terms "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and only describe the present invention, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention; in addition, in the present embodiment, if the connection or fixing manner between the components is not specifically described, the connection or fixing manner may be a bolt fixing manner, a welding fixing manner, a pin fixing manner, or the like, which is commonly used in the prior art, and therefore, detailed description thereof is omitted in this embodiment.

As shown in fig. 1-2, the present embodiment provides a gas turbine blade bearing seat, including a base 1 disposed in a plate shape, and a first accommodating cavity is formed on an upper end surface of the base 1, where the first accommodating cavity in the present embodiment is a first groove 2, the first groove 2 is disposed along a length direction of the base 1, and the first accommodating cavity is used for placing a moving blade; specifically, the blade root of a single moving blade is placed in the first groove 2 so as to complete the placement or fixation of the blade, the upper end surface of the base 1 is also provided with a second accommodating cavity for placing a stationary blade, and particularly, the shroud of the stationary blade is placed in the second accommodating cavity so as to complete the placement or fixation of the stationary blade; the second accommodating cavity takes the axis of the first groove 2 as a datum line and intersects with the first accommodating cavity. When the first accommodating cavity and the second accommodating cavity are intersected or overlapped with each other, the bearing seat can be used for placing the moving blades and the static blades, the blades with different specifications do not need to be placed by using different bearing seats, and meanwhile, the volume of the base 1 can be further reduced. Of course, the first receiving cavity and the second receiving cavity are separated from each other on the base 1, and the functions of placing both the rotor blade and the stator blade on one base 1 can be realized.

As shown in fig. 1-2, in a preferred embodiment, the second accommodating cavity comprises second grooves 3 respectively located at two ends of the first groove 2, and the second grooves 3 are mutually symmetrical with each other. When placing specification for 1 section stationary blade on base 1, be located two shroud blocks respectively on 1 section stationary blade and go into two second recesses 3 in, can accomplish placing and fixing 1 section stationary blade this moment.

As shown in fig. 1-2, in a preferred embodiment, the second accommodating cavity further includes third grooves 4 respectively located at two ends of the first groove 2, and the third grooves 4 are mutually symmetrical with each other. The two sides of the first groove 2 are respectively provided with a fourth groove 5, the fourth grooves 5 are centrosymmetric, and the fourth grooves 5 are positioned between the second or third grooves 4. When placing specification for 2 sections of stationary blades on base 1, two shroud rings that are located on 2 sections of stationary blades are blocked into two third grooves 4 respectively, and two outer peripheral rings on 2 sections of stationary blades are blocked into fourth grooves 5 simultaneously, and the placing and fixing of 2 sections of stationary blades can be completed.

As shown in fig. 1-2, the third groove 4 and the second groove 3 are overlapped with each other, and similarly, after the third groove 4 and the second groove 3 are overlapped with each other, the volume of the base 1 can be reduced after blades of various specifications can be placed, and the width of the third groove is larger than that of the second groove 3; of course, when the third groove 4 and the second groove 3 are separated from each other, the placement and fixation of the stationary blades with different specifications can be realized similarly. The second groove 3 and the third groove 4 are obliquely arranged relative to the first groove 2; the fourth grooves 5 are all parallel to the first grooves 2 so as to be fixed on the base in correspondence with the shrouds of the stator blades. First recess 2 is the trapezoidal setting of falling, and the degree of depth of first recess 2 is greater than the degree of depth of second recess 3, third recess 4, fourth recess 5, because the blade root of moving blade is longer relatively, can keep the moving blade to place or fix the stability on base 1 after the bottom department extension maximize of base 1 by the degree of depth of first recess 2. The length of the second groove 3 is greater than the length of the third groove 4.

The above is only the preferred embodiment of the present invention, and not the scope of the present invention, all the equivalent structures or equivalent flow changes made by the contents of the specification and the drawings or the direct or indirect application in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A gas turbine blade bearing seat is characterized in that: the movable blade bearing device comprises a platy base, wherein a first accommodating cavity is formed in the upper end face of the base, the first accommodating cavity is a first groove, the first groove is formed in the length direction of the base, and the first accommodating cavity is used for accommodating a movable blade; the upper end surface of the base is also provided with a second accommodating cavity, the second accommodating cavity is used for placing a stationary blade, and the second accommodating cavity is arranged along the length direction of the base and partially overlapped with the first accommodating cavity;

2. The gas turbine blade carrier of claim 1 wherein: the second accommodating cavity comprises second grooves which are respectively positioned at two ends of the first groove, and the two second grooves are centrosymmetric.

3. The gas turbine blade carrier of claim 2 wherein: the second accommodating cavity further comprises third grooves respectively located at two ends of the first groove, and the third grooves are centrosymmetric to each other.

4. The gas turbine blade carrier of claim 3 wherein: the third groove and the second groove are overlapped with each other;

or the third groove and the second groove are separated from each other.

5. The gas turbine blade carrier of claim 3 wherein: and fourth grooves are respectively arranged on two sides of the first groove, are centrosymmetric with each other and are positioned between the second grooves or the third grooves.

6. The gas turbine blade carrier of claim 4 wherein: the second groove and the third groove are obliquely arranged relative to the first groove.

7. The gas turbine blade carrier of claim 5, wherein: the fourth grooves are parallel to the first grooves.

8. Gas turbine blade carrier seat according to any one of claims 1 to 7, wherein: the first groove is in an inverted trapezoid shape, and the depth of the first groove is larger than the depth of the second groove, the depth of the third groove and the depth of the fourth groove.

9. The gas turbine blade carrier of claim 8, wherein: the length of the second groove is greater than the length of the third groove.