CN112761734A - Adjusting device for a stationary blade carrier ring of a gas turbine and gas turbine - Google Patents
Adjusting device for a stationary blade carrier ring of a gas turbine and gas turbine Download PDFInfo
- Publication number
- CN112761734A CN112761734A CN202110370130.4A CN202110370130A CN112761734A CN 112761734 A CN112761734 A CN 112761734A CN 202110370130 A CN202110370130 A CN 202110370130A CN 112761734 A CN112761734 A CN 112761734A
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- Prior art keywords
- section
- gas turbine
- shaft
- shaft section
- carrier ring
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Classifications
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an adjusting device for a static blade carrier ring of a gas turbine, which comprises a shaft body and a sliding block, wherein the shaft body comprises a first shaft section and a second shaft section, the cross section of the first shaft section is in a Lelo triangle shape, the first shaft section is provided with a first end and a second end, the second end of the first shaft section is connected with the first end of the second shaft section, and the sliding block is connected with the second end of the second shaft section. The adjusting device of the gas turbine stationary blade carrier ring is small in moment born in the using process and high in structural strength.
Description
Technical Field
The invention relates to the technical field of static blade carrier ring adjustment of a gas turbine, in particular to an adjusting device for a static blade carrier ring of the gas turbine and the gas turbine with the adjusting device.
Background
A stator blade holding ring is arranged in the gas turbine and is mainly used for fixing a stator blade of a gas compressor and a stator blade of a turbine. In order to ensure the normal operation of the gas turbine, the stationary blade carrier ring needs to have good concentricity with the rotor part in the gas turbine, and in the related art, the stationary blade carrier ring needs to be adjusted to be concentric with the rotor part by a special adjusting pin.
In the related art, the adjusting pin is an eccentric pin, the eccentric pin comprises at least two pin shaft sections which are not coaxial, and when the adjusting pin is rotated, the position of the stationary blade retaining ring is adjusted by utilizing an eccentric motion track generated at the end part of the eccentric pin. However, the eccentric pin needs to bear a large action moment in the use process, stress concentration is easily generated at the connecting part of two adjacent pin shaft sections, and the eccentric pin is easy to break in the use process, so that the service life of the eccentric pin is short.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.
To this end, an embodiment of the present invention provides an adjusting apparatus for a gas turbine stationary blade carrier ring, which is less subjected to a moment during use and has a high structural strength.
The adjusting device for the static blade carrier ring of the gas turbine comprises a shaft body, wherein the shaft body comprises a first shaft section and a second shaft section, the cross section of the first shaft section is of a Lelo triangle, the first shaft section is provided with a first end and a second end, the second shaft section is provided with a first end and a second end, and the second end of the first shaft section is connected with the first end of the second shaft section; a slider coupled to the second end of the second shaft section.
Has the advantages that: according to the adjusting device of the gas turbine static blade carrier ring, the moment born by the adjusting device in the using process is small, and the adjusting device has high structural strength.
In some embodiments, one of the slide block and the second end of the second shaft section is provided with a rotation stopping groove, and the other is provided with a rotation stopping part, and the rotation stopping part is matched in the rotation stopping groove to connect the slide block and the shaft body in a rotation stopping way.
In some embodiments, the first end of the first shaft segment is provided with a driving portion protruding from an end surface of the first end of the first shaft segment, the driving portion being prism-shaped.
In some embodiments, the axis of the drive portion and the axis of the shaft body are coaxially arranged.
In some embodiments, the second shaft section includes a large diameter section and a small diameter section, the small diameter section being disposed between the first shaft section and the large diameter section, and the slider is coupled to the large diameter section.
In some embodiments, the large diameter section and the small diameter section are both cylindrical, and the axis of the large diameter section and the axis of the small diameter section are coaxially arranged.
An embodiment of the present invention further provides a gas turbine with the above adjusting device, including: the adjusting device is used for the static blade holding ring of the gas turbine, the cylinder body is sleeved on the outer peripheral side of the static blade holding ring, a through hole is formed in the cylinder body and comprises a square hole section, a matching groove is formed in the outer peripheral surface of the static blade holding ring, the first shaft section is matched in the square hole section, the first shaft section is rotatable in the square hole section, and the sliding block is matched in the matching groove in a rotation stopping mode.
In some embodiments, the outer circumferential side of the cylinder block is provided with a flange protrusion, and the square hole section is provided in the flange protrusion.
In some embodiments, the gas turbine further comprises a flange cover detachably mounted on the flange protrusion, the flange cover for compressively securing the adjusting device between the flange cover and the stationary vane carrier ring.
In some embodiments, the cylinder is a compressor cylinder and the stationary vane carrier ring is a compressor stationary vane carrier ring, or the cylinder is a turbine cylinder and the stationary vane carrier ring is a turbine stationary vane carrier ring.
Drawings
FIG. 1 is a schematic structural diagram of an adjustment apparatus for a gas turbine stationary blade carrier ring according to an embodiment of the present invention.
FIG. 2 is a schematic cross-sectional view of a gas turbine according to an embodiment of the invention.
Fig. 3 is an assembled view of the first shaft segment and directional hole segment of fig. 2.
FIG. 4 is a schematic cross-sectional view of the gas turbine engine of FIG. 2.
Reference numerals:
the adjusting device 100;
a shaft body 1; a first shaft section 11; a second shaft section 12; a small diameter section 121; a large diameter section 122; a drive section 13; a slide block 2;
a cylinder block 200;
a flange projection 3; a through hole 4; a square hole section 41;
a stationary blade carrier ring 300;
a fitting groove 5; a flange cover 6;
the lyo triangle center trajectory 400.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1, an adjusting apparatus 100 (hereinafter, referred to as an adjusting apparatus 100) of a stationary blade carrier ring of a gas turbine according to an embodiment of the present invention includes a shaft body 1 and a slider 2.
The shaft body 1 comprises a first shaft section 11 and a second shaft section 12, wherein the cross section of the first shaft section 11 is in a Lelo triangle shape, the first shaft section 11 is provided with a first end and a second end, the second shaft section 12 is provided with a first end and a second end, and the second end of the first shaft section 11 is connected with the first end of the second shaft section 12.
As shown in fig. 1, the shaft body 1 extends in the up-down direction, and according to the shape, the shaft body 1 includes a first shaft section 11 and a second shaft section 12 extending in the up-down direction, wherein the first shaft section 11 is located above the second shaft section 12. The first shaft section 11 has a lyocell triangle shape in a horizontal cross section.
It should be noted that the first end of the first shaft segment 11 is the top end of the first shaft segment 11, the second end of the first shaft segment 11 is the bottom end of the first shaft segment 11, the first end of the second shaft segment 12 is the top end of the second shaft segment 12, and the second end of the second shaft segment 12 is the bottom end of the second shaft segment 12.
The bottom end of the first shaft section 11 and the top end of the second shaft section 12 are connected and fixed, for example, the first shaft section 11 and the second shaft section 12 may be integrally formed by casting, or may be connected and fixed by welding.
The slide 2 is connected to a second end of the second shaft section 12. Specifically, the sliding block 2 may be detachably connected to the bottom end of the second shaft section 12, for example, the sliding block 2 may be connected to the second shaft section 12 by a thread assembly, and of course, in some other embodiments, in a case of convenient installation, the sliding block 2 may also be fixedly connected to the second shaft section 12, for example, the sliding block 2 may be integrally formed with the second shaft section 12, and the sliding block 2 may also be welded and fixed to the second shaft section 12 after assembly.
According to the adjusting device 100 of the embodiment of the invention, after the adjusting device 100 is installed on the gas turbine, the first shaft section 11 of the shaft body 1 can be matched in the square hole of the corresponding cylinder body 200, the slide block 2 can be matched in the matching groove 5 of the stationary blade holding ring 300 in a rotation stopping manner, when the shaft body 1 rotates, the shaft body 1 can drive the slide block 2 to rotate, and under the rotation stopping effect of the slide block 2 and the matching groove 5, the slide block 2 can drive the stationary blade holding ring 300 to move, so that the position of the stationary blade holding ring 300 can be adjusted.
It should be noted that, since the cross section of the first shaft segment 11 is a reuleaux triangle, and the first shaft segment 11 is fitted in the square hole of the cylinder 200, during the rotation of the shaft body 1, due to the actions of the reuleaux triangle and the square hole, the central axis of the shaft body 1 will shift and change in the horizontal direction, as shown in fig. 3, the central axis of the shaft body 1 will move along the central trajectory 400 of the reuleaux triangle, and the central trajectory 400 of the reuleaux triangle is composed of four arcs of four symmetrical ellipses. The horizontal displacement of axis body 1 changes the distance that can reduce between central axis initial position and the 2 stress points of slider to reduced the arm of force and reduced the moment effect of slider 2 to axis body 1, when having avoided adopting the eccentric pin among the correlation technique, the axis of rotation position of eccentric pin is unchangeable and the arm of force that causes the eccentric pin is longer, the moment of force that receives is great the condition, is favorable to prolonging adjusting device 100's life.
In addition, the adjusting device 100 of the embodiment of the invention can be a straight shaft, and does not need to be provided with a plurality of sections of non-coaxial pin shaft sections, so that the problem that stress concentration is easily generated at the joint of two adjacent pin shaft sections of an eccentric pin is avoided, and the adjusting device 100 has higher structural strength.
In some embodiments, one of the slider 2 and the second end of the second shaft section 12 is provided with a rotation stopping groove, and the other is provided with a rotation stopping portion, and the rotation stopping portion is fitted in the rotation stopping groove to connect the slider 2 and the shaft body 1 in a rotation stopping manner.
Specifically, as shown in fig. 4, the slider 2 and the second shaft section 12 are connected in a rotation stopping assembly, for example, the slider 2 may be provided with a rotation stopping groove, the rotation stopping groove may be a square groove, the bottom end (second end) of the second shaft section 12 may be integrally provided with a rotation stopping portion, the rotation stopping portion may be a quadrangular prism, and when the second shaft section 12 and the slider 2 are connected, the rotation stopping portion at the bottom end of the second shaft section 12 may be inserted into the rotation stopping groove of the slider 2.
It will be appreciated that in other embodiments, the anti-rotation slot may be provided at the bottom end of the second shaft section 12 and the anti-rotation portion may be provided on the top surface of the slider 2. The arrangement of the rotation stopping groove and the rotation stopping part facilitates the connection and the disassembly of the shaft body 1 and the sliding block 2.
In some embodiments, the first end of the first shaft segment 11 is provided with a driving portion 13, the driving portion 13 protrudes out of the end surface of the first end of the first shaft segment 11, and the driving portion 13 is prism-shaped.
Specifically, as shown in fig. 1, the driving portion 13 is disposed at a first end of the first shaft segment 11, the driving portion 13 protrudes from a top end surface of the first shaft segment 11, the driving portion 13 may be a hexagonal prism, and when the driving shaft body 1 rotates, a wrench may be connected to the driving portion 13 and drive the driving portion 13 to rotate. The driving portion 13 is provided to facilitate the rotational driving of the shaft body 1.
It is understood that in other embodiments, the driving portion 13 may be a driving groove formed at the top end of the first shaft section 11, and the driving groove may be a hexagonal groove, and when the driving shaft body 1 rotates, an allen wrench may be inserted into the driving groove.
In some embodiments, the axis of the driving portion 13 and the axis of the shaft body 1 are coaxially arranged. Specifically, as shown in fig. 1, in the up-down direction, the rotation axis of the driving portion 13 and the rotation axis of the shaft body 1 are coaxially and collinearly arranged, so that the driving portion 13 and the shaft body 1 can rotate around the same axis, the condition that an eccentric distance exists between the driving shaft and the shaft body 1 is avoided, and the driving synchronism is ensured.
In some embodiments, the second shaft section 12 includes a large diameter section 122 and a small diameter section 121, the small diameter section 121 is disposed between the first shaft section 11 and the large diameter section 122, and the slider 2 is connected to the large diameter section 122.
As shown in fig. 1, the first shaft section 11 can be subdivided into a large diameter section 122 and a small diameter section 121 according to the difference of the horizontal radial dimension, the radial dimension of the large diameter section 122 is larger than that of the small diameter section 121, the top end of the small diameter section 121 is connected with the first shaft section 11, and the bottom end of the small diameter section 121 is connected with the large diameter section 122.
Preferably, the large-diameter section 122 and the small-diameter section 121 are both cylindrical, and the axis of the large-diameter section 122 and the axis of the small-diameter section 121 are coaxially arranged, so that the condition that the large-diameter section 122 and the small-diameter section 121 have eccentricity is avoided, and the motion synchronism is ensured.
It is understood that in other embodiments, the second shaft segment 12 may be prism-shaped. In order to increase the moment arm, a certain eccentric distance may also exist between the second shaft section 12 and the first shaft section 11, and a certain eccentric distance may also exist between the large diameter section 122 and the small diameter section 121 of the second shaft section 12.
A gas turbine according to an embodiment of the present invention is described below.
The gas turbine according to the embodiment of the present invention includes a cylinder block 200, a stationary vane carrier ring 300, and an adjusting device 100, which may be the adjusting device 100 of the stationary vane carrier ring 300 of the gas turbine described in the above embodiment.
As shown in fig. 2 to 4, the cylinder 200 and the stationary blade ring 300 are both annular, the cylinder 200 is fitted around the outer peripheral side of the stationary blade ring 300, and a gap is set between the cylinder 200 and the stationary blade ring 300. Be equipped with through-hole 4 on the cylinder body 200, through-hole 4 runs through the cylinder wall of cylinder body 200 along the radial direction of cylinder body 200, and through-hole 4 can be the shoulder hole, and through-hole 4 can include the great macropore section in aperture and the less micropore section in aperture promptly, and wherein the macropore section can be located the outside of micropore section, and the macropore section is square hole section 41.
The outer peripheral surface of the stationary blade ring 300 is provided with an engagement groove 5, and the shape of the engagement groove 5 is adapted to the shape of the slider 2, for example, when the slider 2 is a rectangular parallelepiped, the engagement groove 5 may be rectangular. The slide block 2 and the stationary blade carrier ring 300 are assembled by the slide block 2 side surface and the groove wall of the fitting groove 5.
The first shaft section 11 is fitted in the square hole section 41, and the first shaft section 11 is rotatable in the square hole section 41, and the slider 2 is fitted in the fitting groove 5 in a rotation-stopping manner. Specifically, the adjusting device 100 is installed between the cylinder 200 and the stationary blade ring 300, after installation, the first shaft section 11 at the top end of the adjusting device 100 is fitted in the square hole section 41, and the small-diameter section 121 of the second shaft section 12 is fitted in the small-diameter section, so that the small-diameter section is located between the first shaft section 11 and the large-diameter section 122 of the adjusting device 100, and in the rotating process of the adjusting device 100, the first shaft section 11 and the large-diameter section 122 can both be stopped against the upper side and the lower side of the small-diameter section, and a limiting effect is achieved. The slider 2 at the bottom end of the adjusting device 100 is engaged in the engaging groove 5 of the stationary blade carrier ring 300 in a rotation-stopping manner.
When the concentricity of the stationary blade carrier ring 300 is poor, the adjusting device 100 is driven to rotate, and the slider 2 of the adjusting device 100 drives the stationary blade carrier ring 300 to move, so that the concentricity of the stationary blade carrier ring 300 can be adjusted.
In some embodiments, the outer circumferential side of the cylinder block 200 is provided with the flange protrusion 3, and the square hole section 41 is provided in the flange protrusion 3. The gas turbine further includes a flange cover 6, the flange cover 6 being detachably mounted on the flange protrusion 3, the flange cover 6 being used to compressively fix the adjusting device 100 between the flange cover 6 and the stationary blade carrier ring 300.
As shown in fig. 2, the flange protrusion 3 is a protrusion provided on the outer peripheral side of the cylinder 200, the through hole 4 of the cylinder 200 penetrates the flange protrusion 3, and the square hole section 41 of the through hole 4 is provided in the flange protrusion 3. As shown in fig. 4, the flange cover 6 may be detachably mounted on the outer end surface of the flange protrusion 3 by bolts, and after the stationary blade carrier ring 300 is positionally adjusted by the adjusting device 100, the flange cover 6 is fixed on the flange protrusion 3, and the adjusting device 100 may be clamped and fixed between the flange cover 6 and the stationary blade carrier ring 300, so that the fixing of the adjusting device 100 may be achieved, and the corrected stationary blade carrier ring 300 may be maintained at the corrected position.
It should be noted that, when the adjusting device 100 is installed between the stationary vane ring 300 and the cylinder block 200, the outer end of the adjusting device 100 is slightly higher than the outer end face of the flange protrusion 3, so that the fitting contact between the adjusting device 100 and the flange cover 6 is ensured. It will be appreciated that in other embodiments, the flange cover 6 may also be provided with protrusions that can be inserted into the square hole sections 41 to ensure snug contact between the flange cover 6 and the adjustment device 100.
It should be noted that, when the driving portion 13 protrudes from the top end surface of the first shaft section 11, the flange cover 6 is further provided with an insertion hole for inserting the driving portion 13, and the insertion hole can play a role of avoiding the driving portion 13.
In some embodiments, the cylinder 200 is a compressor cylinder 200 and the stationary vane carrier ring 300 is a compressor stationary vane carrier ring 300, or the cylinder 200 is a turbine cylinder 200 and the stationary vane carrier ring 300 is a turbine stationary vane carrier ring 300. Specifically, since the concentricity of the stationary blade retaining ring 300 needs to be adjusted for both the compressor and the turbine in the gas turbine, the cylinder 200 may be a compressor cylinder or a compressor cylinder, and the stationary blade retaining ring 300 may be a stationary blade retaining ring of the turbine or a stationary blade retaining ring of the turbine.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. An adjustment device for a stationary vane carrier ring of a gas turbine, comprising:
the shaft body comprises a first shaft section and a second shaft section, the cross section of the first shaft section is of a Lelo triangle, the first shaft section is provided with a first end and a second end, the second shaft section is provided with a first end and a second end, and the second end of the first shaft section is connected with the first end of the second shaft section;
a slider coupled to the second end of the second shaft section.
2. The adjusting apparatus for a stationary blade carrier ring for a gas turbine as set forth in claim 1, wherein a rotation stopping groove is provided on one of said slider and said second end of said second shaft section, and a rotation stopping portion is provided on the other, said rotation stopping portion being fitted in said rotation stopping groove to connect said slider and said shaft body in rotation stopping.
3. The adjustment device for a gas turbine stationary blade carrier ring according to claim 1, characterized in that the first end of the first shaft section is provided with a drive portion, which projects beyond an end face of the first end of the first shaft section, the drive portion being prism-shaped.
4. The adjusting apparatus for a stationary blade carrier ring of a gas turbine according to claim 3, characterized in that an axis of the driving portion and an axis of the shaft body are coaxially arranged.
5. The adjustment device for a gas turbine stationary vane carrier ring according to any one of claims 1 to 4, characterized in that the second shaft section comprises a large diameter section and a small diameter section, the small diameter section being provided between the first shaft section and the large diameter section, the slider being connected to the large diameter section.
6. The adjustment device for a stationary blade carrier ring of a gas turbine according to claim 5, wherein the large diameter section and the small diameter section are each cylindrical, and an axis of the large diameter section and an axis of the small diameter section are arranged coaxially.
7. A gas turbine engine, comprising: the adjusting device for the static blade retaining ring of the gas turbine is as claimed in any one of claims 1 to 6, the cylinder body is sleeved on the outer peripheral side of the static blade retaining ring, a through hole is formed in the cylinder body, the through hole comprises a square hole section, a matching groove is formed in the outer peripheral surface of the static blade retaining ring, the first shaft section is matched in the square hole section, the first shaft section is rotatable in the square hole section, and the sliding block is in rotation stopping matching in the matching groove.
8. The gas turbine according to claim 7, wherein the outer peripheral side of the cylinder block is provided with a flange projection, and the square hole section is provided in the flange projection.
9. The gas turbine of claim 8, further comprising a flange cover removably mounted on said flange protrusion, said flange cover for compressively securing said adjusting means between said flange cover and said stationary vane carrier ring.
10. The gas turbine according to claim 7, wherein the cylinder is a compressor cylinder and the stationary vane carrier ring is a compressor stationary vane carrier ring, or the cylinder is a turbine cylinder and the stationary vane carrier ring is a turbine stationary vane carrier ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110370130.4A CN112761734B (en) | 2021-04-07 | 2021-04-07 | Adjusting device for a stationary blade carrier ring of a gas turbine and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110370130.4A CN112761734B (en) | 2021-04-07 | 2021-04-07 | Adjusting device for a stationary blade carrier ring of a gas turbine and gas turbine |
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| Publication Number | Publication Date |
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| CN112761734A true CN112761734A (en) | 2021-05-07 |
| CN112761734B CN112761734B (en) | 2021-07-20 |
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