CN216278027U - Gas turbine inlet guide vane mounting structure and gas turbine - Google Patents
Gas turbine inlet guide vane mounting structure and gas turbine Download PDFInfo
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- CN216278027U CN216278027U CN202120688409.2U CN202120688409U CN216278027U CN 216278027 U CN216278027 U CN 216278027U CN 202120688409 U CN202120688409 U CN 202120688409U CN 216278027 U CN216278027 U CN 216278027U
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Abstract
The utility model discloses a gas turbine inlet guide vane mounting structure and a gas turbine, wherein the gas turbine inlet guide vane mounting structure comprises an air inlet cylinder, an inlet blade structure, an adjusting gear and a threaded connection structure, a mounting cavity is formed in the air inlet cylinder and used for mounting a main shaft of the gas turbine, an avoidance hole is formed in the side wall of the mounting cavity in a penetrating mode, the inlet blade structure comprises a mounting shaft and a blade fixedly connected with the mounting shaft, the blade is arranged between the air inlet cylinder and the main shaft of the gas turbine, one end of the mounting shaft penetrates through the avoidance hole and protrudes out of the outer side wall of the air inlet cylinder to form a mounting shaft end, the adjusting gear is arranged at the mounting shaft end and rotates coaxially with the mounting shaft end, the threaded connection structure is arranged between the mounting shaft and the adjusting gear and used for limiting the axial relative movement and the circumferential relative movement between the mounting shaft and the adjusting gear so as to avoid the axial movement of the mounting shaft, thereby ensuring that the clearance between the blade and the air inlet cylinder is in a reasonable range.
Description
Technical Field
The utility model relates to the field of gas turbines, in particular to a gas turbine inlet guide vane mounting structure and a gas turbine.
Background
Gas turbine Inlet Guide Vanes (IGVs) are used to control the flow of air into the gas turbine. IGV devices consist of a set of airfoil blades mounted directly in front of the first stage of the gas turbine. The root of the blade passes through the gas turbine casing and is connected to a pinion. A circular ring-shaped linkage gear ring arranged around the gas turbine shell is meshed with the pinion, and the linkage gear ring drives the blades to rotate through the pinion so as to increase or reduce the effective inlet area of the gas turbine. In the long-term use and operation process of the gas turbine, due to the fact that a fixing structure is not arranged between the pinion and the blades, the blades can move in the shell of the gas turbine, the gap between the blades and the shell is too small, the problems of blade curling, cylinder body collision and abrasion and the like are caused, and the normal work of a system is influenced. Therefore, how to control the clearance between the inlet guide vane and the outer casing of the gas turbine is an urgent problem to be solved.
SUMMERY OF THE UTILITY MODEL
The utility model mainly aims to provide a gas turbine inlet guide vane mounting structure and a gas turbine, and aims to solve the problem that a gap between a gas turbine inlet guide vane and a shell is too small.
In order to achieve the above object, the present invention provides an inlet guide vane mounting structure of a gas turbine, including:
the gas inlet cylinder is internally provided with a mounting cavity, the mounting cavity is used for mounting a main shaft of the gas turbine, and the side wall of the mounting cavity is provided with an avoidance hole in a penetrating manner;
the inlet blade structure comprises an installation shaft and a blade fixedly connected with the installation shaft, the blade is arranged between the air inlet cylinder and a main shaft of the gas turbine, and one end of the installation shaft penetrates through the avoidance hole and protrudes out of the outer side wall of the air inlet cylinder to form an installation shaft end;
the adjusting gear is arranged at the mounting shaft end and rotates coaxially with the mounting shaft end, and the adjusting gear is used for being in transmission engagement with the linkage gear ring; and the number of the first and second groups,
and the threaded connection structure is arranged between the mounting shaft and the adjusting gear and used for limiting the axial relative movement and the circumferential relative movement between the mounting shaft and the adjusting gear.
Optionally, the adjusting gear is provided with a mounting hole, and the mounting shaft end is sleeved in the mounting hole;
the threaded connection structure comprises a fixed threaded hole and a fixed screw which are in threaded fit with each other, the fixed threaded hole is partially penetrated through the hole wall of the mounting hole, and the rest part of the fixed threaded hole is arranged on the outer side surface of the mounting shaft end.
Optionally, the fixing threaded holes and the fixing screws are in one-to-one correspondence to form connecting assemblies;
coupling assembling sets up a plurality ofly, and follows the circumference interval of installation axle sets up.
Optionally, the threaded connection structure further includes an auxiliary connection structure, the auxiliary connection structure includes a fixing pin and a fixing hole that are matched with each other, the fixing hole is partially penetrated through the hole wall of the mounting hole, and the rest of the fixing hole is arranged on the outer side surface of the mounting shaft end.
Optionally, the mounting shaft includes a first shaft section located at one end of the vane facing the intake cylinder, a free end of the first shaft section forms the mounting shaft end, a limiting boss is disposed at an end of the first shaft section opposite to the mounting shaft end, and the limiting boss is used for limiting an outward movement stroke of the mounting shaft.
Optionally, the avoiding hole is arranged in a step shape and comprises a first hole section with a larger pore diameter and a second hole section with a smaller pore diameter which are distributed from inside to outside, and a first step surface facing away from the blade is formed between the first hole section and the second hole section;
the end face of the limiting boss abuts against the first step face.
Optionally, the inlet vane structure further includes a thrust washer sleeved on the mounting shaft, and the thrust washer is located between the inner wall surface of the intake cylinder and the end surface of the limiting boss.
Optionally, the mounting shaft includes a second shaft section disposed at an end of the vane facing the intake cylinder, a third shaft section is disposed at an end of the second shaft section, and a shaft diameter of the third shaft section is smaller than a shaft diameter of the second shaft section, so that a step surface facing away from the vane is formed between the second shaft section and the third shaft section, and the step surface abuts against an end surface of the adjusting gear;
the second shaft section is sleeved in the avoiding hole;
the third shaft segment at least partially forms the mounting shaft end.
Optionally, the inlet vane structure further includes a spring washer sleeved at the mounting shaft end, and the spring washer is located between the outer wall surface of the intake cylinder and the end surface of the adjusting gear.
The utility model provides a gas turbine, which comprises a gas turbine inlet guide vane mounting structure, wherein the gas turbine inlet guide vane mounting structure comprises:
the gas inlet cylinder is internally provided with a mounting cavity, the mounting cavity is used for mounting a main shaft of the gas turbine, and the side wall of the mounting cavity is provided with an avoidance hole in a penetrating manner;
the inlet blade structure comprises an installation shaft and a blade fixedly connected with the installation shaft, the blade is arranged between the air inlet cylinder and a main shaft of the gas turbine, and one end of the installation shaft penetrates through the avoidance hole and protrudes out of the outer side wall of the air inlet cylinder to form an installation shaft end;
the adjusting gear is arranged at the mounting shaft end and rotates coaxially with the mounting shaft end, and the adjusting gear is used for being in transmission engagement with the linkage gear ring; and the number of the first and second groups,
and the threaded connection structure is arranged between the mounting shaft and the adjusting gear and used for limiting the axial relative movement and the circumferential relative movement between the mounting shaft and the adjusting gear.
In the technical scheme of the utility model, the inlet blade structure comprises an installation shaft and a blade fixedly connected with the installation shaft, the blade is arranged between the air inlet cylinder and a main shaft of the gas turbine, one end of the installation shaft penetrates through the avoidance hole and protrudes out of the outer side wall of the air inlet cylinder to form an installation shaft end, the adjusting gear is arranged at the installation shaft end and rotates coaxially with the installation shaft end, the adjusting gear is used for being in transmission engagement with a linkage gear ring, the threaded connection structure is arranged between the installation shaft and the adjusting gear, the torque of the adjusting gear is transmitted to the installation shaft through the threaded connection structure to drive the blade fixedly connected with the installation shaft to rotate, so that the air intake amount of the gas turbine is controlled, and meanwhile, the installation shaft and the adjusting gear are fixedly connected through the threaded connection structure, and the mounting shaft is prevented from moving along the axial direction, so that the clearance between the blade and the air inlet cylinder is ensured to be in a reasonable range.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic cross-sectional view of an embodiment of a gas turbine inlet guide vane mounting structure provided in the present invention;
fig. 2 is a front view of the inlet vane structure of fig. 1.
The reference numbers illustrate:
| reference numerals | Name (R) | Reference numerals | Name (R) |
| 100 | Gas turbine inlet guide |
23 | |
| 1 | |
24 | |
| 11 | Avoiding |
25 | |
| 2 | |
3 | Adjusting |
| 21 | |
31 | |
| 211 | |
4 | Threaded |
| 22 | Blade |
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that, if directional indication is involved in the embodiment of the present invention, the directional indication is only used for explaining the relative positional relationship, the motion situation, and the like between the components in a certain posture, and if the certain posture is changed, the directional indication is changed accordingly.
In addition, if there is a description of "first", "second", etc. in an embodiment of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is 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 addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
In the long-term use and operation process of the gas turbine, due to the fact that a fixing structure is not arranged between the pinion and the blades, the blades can move in the shell of the gas turbine, the gap between the blades and the shell is too small, the problems of blade curling, cylinder body collision and abrasion and the like are caused, and the normal work of a system is influenced.
In view of this, the present invention provides a gas turbine including a gas turbine inlet guide vane mounting structure, which is within the protection scope of the present invention, wherein fig. 1 and 2 are schematic structural views of the gas turbine inlet guide vane mounting structure provided by the present invention.
Please refer to fig. 1, the gas turbine inlet guide vane mounting structure 100 includes an inlet cylinder 1, an inlet blade 22 structure 2, a regulating gear 3 and a threaded connection structure 4, a mounting cavity is formed inside the inlet cylinder 1, the mounting cavity is used for mounting a main shaft of the gas turbine, a relief hole 11 is formed through a side wall of the mounting cavity, the inlet blade 22 structure 2 includes a mounting shaft 21 and a blade 22 fixedly connected with the mounting shaft 21, the blade 22 is used for being disposed between the inlet cylinder 1 and the main shaft of the gas turbine, one end of the mounting shaft 21 passes through the relief hole 11 and protrudes out of an outer side wall of the inlet cylinder 1 to form a mounting shaft 21 end, the regulating gear 3 is disposed at the mounting shaft 21 end and rotates coaxially with the mounting shaft 21 end, the regulating gear 3 is used for being engaged with a linked gear ring in a transmission manner, the threaded connection structure 4 is disposed between the mounting shaft 21 and the regulating gear 3, to limit the axial and circumferential relative movements between the mounting shaft 21 and the adjusting gear 3.
In the technical solution of the present invention, the inlet vane 22 structure 2 includes an installation shaft 21 and a vane 22 fixedly connected to the installation shaft 21, the vane 22 is configured to be disposed between the intake cylinder 1 and a main shaft of the gas turbine, one end of the installation shaft 21 passes through the relief hole 11 and protrudes out of an outer side wall of the intake cylinder 1 to form an installation shaft 21 end, the adjusting gear 3 is disposed at the installation shaft 21 end and rotates coaxially with the installation shaft 21 end, the adjusting gear 3 is configured to be engaged with a linked gear ring in a transmission manner, the threaded connection structure 4 is disposed between the installation shaft 21 and the adjusting gear 3, and the torque of the adjusting gear 3 is transmitted to the installation shaft 21 through the threaded connection structure 4 to drive the vane 22 fixedly connected to the installation shaft 21 to rotate, so as to control an intake air amount of the gas turbine, meanwhile, the mounting shaft 21 is fixedly connected with the adjusting gear 3 through the threaded connection structure 4, so that the mounting shaft 21 is prevented from moving along the axial direction, and the gap between the blade 22 and the air inlet cylinder 1 is ensured to be in a reasonable range.
Further, the adjusting gear 3 is provided with a mounting hole 31, the end of the mounting shaft 21 is sleeved in the mounting hole 31, the threaded connection structure 4 comprises a fixing threaded hole and a fixing screw which are in threaded fit with each other, the fixing threaded hole is partially arranged through the hole wall of the mounting hole 31, and the rest part is arranged on the outer side surface of the end of the mounting shaft 21.
Further, fixed screw hole with the set screw one-to-one is coupling assembling, coupling assembling sets up a plurality ofly, and follows the circumference interval of installation axle 21 sets up, so sets up, through setting up a plurality ofly coupling assembling, in order to strengthen installation axle 21 with adjusting gear 3's connection.
In order to guarantee in time with adjusting gear 3's moment of torsion in time transmits for installation axle 21, threaded connection structure 4 still includes supplementary connection structure, supplementary connection structure includes the fixed pin and the fixed orifices of mutually supporting, the fixed orifices portion runs through to be located the pore wall of installation hole 31, other parts are located the lateral surface of installation axle 21 end, so set up, through increasing supplementary connection structure, in order to strengthen adjusting gear 3 with install the circumference of axle 21 and connect, ensure in time with adjusting gear 3's moment of torsion is transmitted for installation axle 21.
In order to fixedly connect the vane 22 with the mounting shaft 21, the mounting shaft 21 includes a first shaft section disposed at one end of the vane 22 facing the intake cylinder 1, a free end of the first shaft section forms the mounting shaft 21 end, a limiting boss 23 is disposed at an end of the first shaft section opposite to the mounting shaft 21 end, and the limiting boss 23 is used for limiting an outward moving stroke of the mounting shaft 21, so that the vane 22 and the mounting shaft 21 are respectively mounted on two sides of the limiting boss 23 by the limiting boss 23, which facilitates fixedly connecting the vane 22 with the mounting shaft 21, and at the same time, the mounting shaft 21 can be quickly positioned by the limiting boss 23 during mounting, which facilitates the mounting of the inlet vane 22 structure 2.
Further, dodge hole 11 and be the step setting, including the great first hole section in aperture and the less second hole section in aperture that distribute from inside to outside, first hole section with form between the second hole section dorsad the first step face of blade 22, wherein, the terminal surface of spacing boss 23 support tightly in first step face, so set up, through first hole section, help with spacing boss 23 is installed fast and is in place.
In order to control the gap between the limiting boss 23 and the intake cylinder 1, the inlet vane 22 structure 2 further includes a thrust washer 24 sleeved on the mounting shaft 21, the thrust washer 24 is located between the inner wall surface of the intake cylinder 1 and the end surface of the limiting boss 23, and by setting the thrust washer 24, the gap between the limiting boss 23 and the intake cylinder 1 is conveniently adjusted, and then the gap between the vane 22 and the intake cylinder 1 is controlled.
In order to facilitate the installation adjusting gear 3, installation axle 21 is including locating blade 22 moves towards the second axle section of the one end of intake cylinder 1, the tip of second axle section is equipped with the third axle section, the diameter of axle of third axle section is less than the diameter of axle of second axle section, so that the second axle section with form between the third axle section and deviate from the step face of blade 22, the step face supports tightly adjusting gear 3's terminal surface, wherein, the second axle section cover is located in dodging hole 11, the third axle section at least part forms installation axle 21 end, so set up, through the second axle section with the step face that forms between the third axle section, help will fast adjusting gear 3 install in installation axle 21.
In order to control the gap between the adjusting gear 3 and the intake cylinder 1, the inlet vane 22 structure 2 further includes a spring washer 25 sleeved on the end of the mounting shaft 21, the spring washer 25 is located between the outer wall surface of the intake cylinder 1 and the end surface of the adjusting gear 3, and thus, the gap between the adjusting gear 3 and the intake cylinder 1 is controlled by the spring washer 25, so as to avoid friction between the adjusting gear 3 and the intake cylinder 1.
The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications and equivalents made by the contents of the present specification and drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A gas turbine inlet guide vane mounting structure, comprising:
the gas inlet cylinder is internally provided with a mounting cavity, the mounting cavity is used for mounting a main shaft of the gas turbine, and the side wall of the mounting cavity is provided with an avoidance hole in a penetrating manner;
the inlet blade structure comprises an installation shaft and a blade fixedly connected with the installation shaft, the blade is arranged between the air inlet cylinder and a main shaft of the gas turbine, and one end of the installation shaft penetrates through the avoidance hole and protrudes out of the outer side wall of the air inlet cylinder to form an installation shaft end;
the adjusting gear is arranged at the mounting shaft end and rotates coaxially with the mounting shaft end, and the adjusting gear is used for being in transmission engagement with the linkage gear ring; and the number of the first and second groups,
and the threaded connection structure is arranged between the mounting shaft and the adjusting gear and used for limiting the axial relative movement and the circumferential relative movement between the mounting shaft and the adjusting gear.
2. The gas turbine inlet guide vane mounting structure of claim 1, wherein the adjusting gear is provided with a mounting hole, and the mounting shaft end is sleeved in the mounting hole;
the threaded connection structure comprises a fixed threaded hole and a fixed screw which are in threaded fit with each other, the fixed threaded hole is partially penetrated through the hole wall of the mounting hole, and the rest part of the fixed threaded hole is arranged on the outer side surface of the mounting shaft end.
3. The gas turbine inlet guide vane mounting structure of claim 2, wherein the fixing threaded holes and the fixing screws are one-to-one in connection assemblies;
coupling assembling sets up a plurality ofly, and follows the circumference interval of installation axle sets up.
4. The gas turbine inlet guide vane mounting structure of claim 2, wherein the threaded connection further comprises an auxiliary connection structure, the auxiliary connection structure comprises a fixing pin and a fixing hole which are matched with each other, the fixing hole is partially penetrated through the hole wall of the mounting hole, and the rest part of the fixing hole is arranged on the outer side surface of the mounting shaft end.
5. The gas turbine inlet guide vane mounting structure of claim 1, wherein the mounting shaft includes a first shaft section disposed at an end of the blade facing the inlet cylinder, a free end of the first shaft section forms the mounting shaft end, and an end of the first shaft section opposite to the mounting shaft end is provided with a limit boss for limiting an outward movement stroke of the mounting shaft.
6. The mounting structure of the inlet guide vane of the gas turbine according to claim 5, wherein the avoiding hole is arranged in a step shape and comprises a first hole section with a larger hole diameter and a second hole section with a smaller hole diameter which are distributed from inside to outside, and a first step surface facing away from the blade is formed between the first hole section and the second hole section;
the end face of the limiting boss abuts against the first step face.
7. The gas turbine inlet guide vane mounting structure of claim 5, wherein the inlet vane structure further comprises a thrust washer sleeved on the mounting shaft, the thrust washer being located between an inner wall surface of the inlet cylinder and an end surface of the limit boss.
8. The gas turbine inlet guide vane mounting structure of claim 1, wherein the mounting shaft comprises a second shaft section provided at an end of the blade facing the inlet cylinder, a third shaft section is provided at an end of the second shaft section, and a shaft diameter of the third shaft section is smaller than that of the second shaft section, so as to form a step surface facing away from the blade between the second shaft section and the third shaft section, and the step surface abuts against an end surface of the adjusting gear;
the second shaft section is sleeved in the avoiding hole;
the third shaft segment at least partially forms the mounting shaft end.
9. The gas turbine inlet guide vane mounting structure of claim 1, wherein the inlet vane structure further comprises a spring washer sleeved on the mounting shaft end, the spring washer being located between an outer wall surface of the inlet cylinder and an end surface of the adjusting gear.
10. A gas turbine engine comprising the gas turbine engine inlet guide vane mounting structure of any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120688409.2U CN216278027U (en) | 2021-04-02 | 2021-04-02 | Gas turbine inlet guide vane mounting structure and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120688409.2U CN216278027U (en) | 2021-04-02 | 2021-04-02 | Gas turbine inlet guide vane mounting structure and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216278027U true CN216278027U (en) | 2022-04-12 |
Family
ID=81001350
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120688409.2U Active CN216278027U (en) | 2021-04-02 | 2021-04-02 | Gas turbine inlet guide vane mounting structure and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216278027U (en) |
-
2021
- 2021-04-02 CN CN202120688409.2U patent/CN216278027U/en active Active
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