CN113898414A - Reinforcing structure for preventing thermal vibration deformation of high-pressure rotor of gas turbine - Google Patents
Reinforcing structure for preventing thermal vibration deformation of high-pressure rotor of gas turbine Download PDFInfo
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- CN113898414A CN113898414A CN202111494677.1A CN202111494677A CN113898414A CN 113898414 A CN113898414 A CN 113898414A CN 202111494677 A CN202111494677 A CN 202111494677A CN 113898414 A CN113898414 A CN 113898414A
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
Abstract
The invention belongs to the technical field of gas turbines, and particularly relates to a reinforcing structure for preventing thermal vibration deformation of a high-pressure rotor of a gas turbine, which comprises a transfer shaft, an adjusting pad and a lining; the high-pressure rotor of the gas turbine is provided with a grate disc, and the grate disc is connected to the high-pressure turbine through a drum shaft; a turbine shaft is connected in the high-pressure turbine; the bushing is arranged at one end of the transfer shaft; one end of the transfer shaft is abutted against the center of the grate disc through the bushing; the other end of the transfer shaft extends to the center of the high-pressure turbine and abuts against the turbine shaft; the adjusting pad is arranged at the joint of the bushing and the transfer shaft and transmits axial supporting force. The original structures of the high-pressure rotor and the high-pressure turbine are utilized, the adverse effect of the coupling change of the elastic modulus and the thermal stress of the parts on the rigidity of the high-pressure rotor is effectively weakened, the problem of deformation caused by high temperature and high temperature difference in different working stages of the engine is reduced, and the safe and reliable operation of the gas turbine is powerfully guaranteed.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a reinforcing structure for preventing thermal vibration deformation of a high-pressure rotor of a gas turbine.
Background
A gas turbine is an internal combustion type power machine that converts energy of a gas into useful work, and is widely used in various fields, such as: the power generation device is applied to the field of civil power generation or used as a power device in an airplane or a large ship. The working process of the gas turbine is as follows: the air compressor continuously sucks air from the atmosphere and compresses the air; the compressed air enters a combustion chamber, is mixed with gas sprayed in the combustion chamber and then is combusted to form high-temperature gas, then the high-temperature gas flows into a gas turbine to expand and do work, and the high-temperature gas is used for pushing the turbine to drive a gas compressor to rotate together; the gas turbine is a device with good cleaning performance and high efficiency, and has the advantages of small volume, low weight and the like.
Since the advent of the gas turbine, the gas turbine has gained wide acceptance both at home and abroad due to its advantages of high power, small volume, fast start, stable operation and the use of various fuels, and a great deal of research work has been carried out by many scientific and technological workers both at home and abroad, and has been developed in a leap-over manner in a short time. The merits of the state of the art in gas turbines also reflect both the state of the art and the military strength.
The temperature of the parts of the gas turbine is high during operation, and the temperature of the parts at different positions and even different areas of the same part can have large difference; during the unused stages of the gas turbine during startup, high speed operation, and shutdown, the temperatures at various components on the gas turbine will vary significantly. For example: after the gas turbine is stopped, the heat in the gas turbine can be dissipated outwards through the outer casing, the temperature of the outer structure of the gas turbine is gradually reduced quickly, the temperature of the inner structure of the gas turbine is still high, the temperature reduction speed of the inner structure of the gas turbine is low, the whole gas turbine is in an external cold and internal hot state, and in addition, the temperatures of parts in all regions in the axial direction of the gas turbine are different.
The above phenomenon is particularly apparent in the area where the high-pressure rotor and the high-pressure turbine of the high-pressure compressor are located. And due to the thermal stress generated when the temperature distribution is not uniform, the high-pressure rotor is subjected to certain thermal bending, so that the rigidity matrix inside the gas turbine is changed, namely: in the case of a large temperature difference, the connection between the high-pressure rotor and the high-pressure turbine and the component itself may be deformed due to the large thermal vibration, and when the deformation is serious, the safe operation of the gas turbine may be affected.
At present, domestic treatment measures for solving the problem of thermal vibration deformation possibly generated by a high-pressure rotor are single, on one hand, the structures of the high-pressure rotor and a high-pressure turbine are changed, and elements such as the shape, the size and the like of parts are redesigned, for example: the structure of a blade disc or a blade of the high-pressure rotor is changed, so that the rigidity in the high-pressure rotor is reasonably distributed; on the other hand, the technician may also improve the deformation resistance of the component itself by changing the material of the component, such as: the material of the part with higher temperature and larger temperature difference change is changed into high-temperature powder alloy, thereby reducing the adverse effect generated by thermal stress and thermal bending deformation generated by high temperature and temperature difference. The two solutions have certain disadvantages, wherein the scheme of changing the structural form has high working difficulty and large workload, and greatly increases the research and development cost; the scheme of changing the material brings high cost and unknown uncertain factors, and certain negative effects are caused to the working performance and reliability of the gas turbine.
Therefore, there is a need for a structure that can reinforce the connection structure between the high-pressure rotor and the high-pressure turbine of an existing gas turbine, thereby reducing costs and difficulties.
Disclosure of Invention
In order to solve the problems existing in the prior art, the scheme provides a reinforcing structure for preventing the thermal vibration deformation of a high-pressure rotor of a gas turbine.
The technical scheme adopted by the invention is as follows:
a reinforcement structure for preventing thermal vibration deformation of a high-pressure rotor of a gas turbine comprises a transfer shaft, an adjusting pad and a bushing;
the high-pressure rotor of the gas turbine is provided with a grate disc, and the grate disc is connected to the high-pressure turbine through a drum shaft; a turbine shaft is connected in the high-pressure turbine;
the bushing is arranged at one end of the transfer shaft; one end of the transfer shaft is abutted against the center of the grate disc through the bushing; the other end of the transfer shaft extends to the center of the high-pressure turbine and abuts against the turbine shaft; the adjusting pad is arranged at the joint of the bushing and the transfer shaft and transmits axial supporting force.
In the structure, when the high-pressure rotor deforms due to thermal vibration, the axial supporting force is transmitted by the drum shaft and the adapter shaft at the same time, the shape change of the high-pressure rotor due to thermal vibration deformation and the change of the relative position of the high-pressure rotor and the high-speed turbine are reduced, the stability of the high-pressure rotor structure is improved and guaranteed, and the support position of the adapter shaft is different from the connection position of the drum shaft, so that a local lever effect is formed between the high-pressure rotor and the adapter shaft, the connection position of the drum shaft is used as a fulcrum, the support of the adapter shaft is utilized, and the problem that the deformation of the outer side of the grate disc and the deformation of the disc body of the grate disc exceed the standard due to the phenomenon of thermal vibration is solved.
As an alternative and complementary design to the above-described reinforcing structure, the adapter shaft includes two sections of a rotor-side shaft body and a turbine-side shaft body, which are butt-joined. In the supplementary design, the adapter shaft is designed into two sections, the two sections are connected in a butt joint mode, a first butt joint part is arranged at the position, used for butting the turbine side shaft body, of the rotor side shaft body, the butt joint part is in an annular step shape, and a corresponding second butt joint part is arranged at one end, used for butting the first butt joint part, of the turbine side shaft body, so that the turbine side shaft body can be butted to the first butt joint part of the rotor side shaft body in a splicing mode. In addition, because the adapter shaft adopts a two-section structure, the adapter shaft can be conveniently processed, the requirements of different positions on the performances of rigidity, hardness and the like and material selection can be met, and the rejection rate and high cost caused by processing parts with longer length can be avoided.
As an alternative structure and a supplementary design of the above reinforcing structure, a second support portion extending radially outward is provided on the rotor-side shaft body; the joint of the drum shaft and the high-pressure turbine is annular; the outer edge of the second supporting part is abutted against the inner side of the joint of the drum shaft and the high-pressure turbine. The outside border of this second supporting part extends towards the junction of drum shaft and high-pressure turbine to can support in the inboard of this junction, thereby provide radial holding power, the temperature that is higher or the temperature difference change is great when this junction, and during the trend of deformation takes place because of the thermal vibration phenomenon, through the support of this second supporting part, can offset the power that this junction deformation takes place, thereby make this junction can not take place to warp because of thermal vibration.
As an alternative and complementary design to the above-described reinforcement structure, the turbine-side shaft body bears against the end face of the turbine shaft and provides a radial supporting force for the high-pressure turbine. In the scheme, the turbine side shaft body provides a supporting force by the end face of the turbine shaft, and the supporting force on the turbine shaft is transmitted to the labyrinth disc through the transfer shaft.
As an alternative configuration and a complementary design of the above-described reinforcing structure, a first support portion is provided at one end of the coupling shaft connected to the bush, the first support portion radially protruding from the outer circumferential wall of the rotor-side shaft body and having a disk shape. The thickness of the shaft body of the adapter shaft at the first supporting part is thicker, and the adapter shaft transmits axial supporting force through the first supporting part, so that the grate disc can be axially abutted tightly; when the labyrinth plate itself and the components of the high-pressure rotor are deformed due to thermal vibration, the tendency of deformation can be suppressed by the adapter shaft.
As an alternative structure and a supplementary design of the reinforcing structure, axial convex teeth are arranged at the edge of the end surface at one side of the bushing and extend out along the axial direction of the bushing; the outer edge of the first supporting part is provided with a groove corresponding to the axial convex tooth, and the axial convex tooth provides radial inward supporting force for the rotor side shaft body. The axial convex tooth of setting in this scheme provides radial inward holding power to first supporting part to avoid first supporting part to damage under the centrifugal force effect of high-speed rotation.
As an alternative structure and a supplementary design of the reinforcing structure, the edge of the bushing is provided with radial convex teeth; the radial convex teeth radially extend outwards and are abutted against the first supporting part so as to axially transfer force. Radial convex teeth arranged on the bushing in the scheme can transmit supporting force of a rotor side shaft body to the center of the grate disc, and meanwhile, the bushing is mainly used for connecting the grate disc and the adapter shaft.
As an alternative to and in addition to the reinforcing structure described above, the outer circumferential surface of the bushing is inclined so that it can be fitted onto the center of the labyrinth plate. The inclined structural design can enable the grating disc to be attached to the grating disc more, so that the alignment of the transfer shaft and the grating disc is assisted.
As an alternative structure and a supplementary design of the reinforcing structure, the transfer shaft is in a hollow pipe sleeve shape; a cavity is arranged between the transfer shaft and the drum shaft, a second supporting part arranged on the transfer shaft divides the cavity into a front cavity and a rear cavity, and a through hole is arranged on the second supporting part to communicate the two cavities. The design of each cavity and cavity of the structure can reduce the weight of the high-pressure rotor and the high-pressure turbine, and air circulation and heat dissipation can be carried out through the cavities.
As an alternative structure and a supplementary design of the reinforcing structure, the bushing and the adapter shaft are made of high-temperature-resistant powder alloy materials, and the adjusting pad is made of titanium alloy materials. The titanium alloy adjusting pad has excellent rigidity, so that the titanium alloy adjusting pad can effectively reinforce the thermal stress deformation of the front and rear parts and effectively connect the front and rear parts. In addition, the characteristics that the thermal stress and the thermal bending deformation of the high-temperature powder alloy generated under the conditions of high temperature and high temperature difference are small are fully utilized by the bushing and the adapter shaft, and the parts such as a high-pressure rotor, a high-pressure turbine and the like are reinforced on the premise of effectively improving the performance of the parts.
The invention has the beneficial effects that:
1. the scheme reasonably utilizes the original structures of the high-pressure rotor and the high-pressure turbine, constructs a novel and unique structure with high practical value, effectively weakens the adverse effect of the coupling change of the elastic modulus and the thermal stress of the parts on the rigidity of the high-pressure rotor, and reduces the problem of deformation caused by high temperature and high temperature difference in different working stages of the engine to the maximum extent, thereby powerfully ensuring the safe and reliable operation of the gas turbine;
2. in the scheme, structures such as a transfer shaft, an adjusting pad and a bush are added on a crude oil structure of the gas turbine, and the radial axial support reinforcement of the high-pressure rotor and the high-pressure turbine can be realized, so that the deformation resistance of the high-pressure rotor and the high-pressure turbine is improved; in addition, the bushing is of a bolt-free structure, so that the original grate disc structure does not need to be changed, and the cost and the installation mode are optimized; the groove on the first supporting part at the outer side of the end part of the adapter shaft can be matched with a corresponding convex tooth structure on the bushing to realize radial and axial supporting reinforcement;
3. in the scheme, the cavity formed by the bushing, the adjusting pad, the transfer shaft, the high-pressure rotor, the high-pressure turbine, the grate disc and the like is reasonable in layout, and the heat can be effectively dissipated outwards; the bushing and the adapter shaft are made of high-temperature-resistant powder alloy materials, and the adjusting pad is made of titanium alloy materials, so that the deformation resistance of the part is effectively enhanced.
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.
FIG. 1 is a view showing a state of use of a reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation in the present embodiment;
FIG. 2 is a view showing a coupling position of a drum shaft and a rotor-side shaft body;
FIG. 3 is a perspective view showing a connected state of a drum shaft and a rotor-side shaft body;
FIG. 4 is an enlarged view of the attachment position of the adjustment pad;
FIG. 5 is a perspective view of a rotor-side shaft body;
fig. 6 is a perspective view of the bushing.
In the figure: 1-a high pressure turbine; 2-turbine side shaft body; 3-drum shaft; 4-rotor side shaft body; 41-a first support part; 42-shaft body; 43-a second support; 44-a groove; 45-a first docking portion; 5-a grate disc; 6-a lining; 61-embedding grooves; 62-axial lobes; 63-radial lobes; 7-adjusting the cushion; 8-a high pressure rotor; 9-turbine shaft.
Detailed Description
The technical solutions in the embodiments will be described clearly and completely with reference to the accompanying drawings, and the described embodiments are only a part of the embodiments, but not all embodiments, and all other embodiments obtained by those skilled in the art without creative efforts will belong to the protection scope of the present solution based on the embodiments in the present solution.
Example 1
As shown in fig. 1 to 6, the present embodiment designs a reinforcing structure of a high-pressure rotor of a gas turbine against thermal vibration deformation.
During the rotation of the high-pressure rotor 8 and the high-pressure turbine 1 in the respective operating regions, different temperature conditions occur during the startup phase of the gas turbine, for example, higher temperatures or higher temperature differences occur. And thermal stress will be generated when the temperature distribution is not uniform, thereby causing some thermal bending of the high-pressure rotor 8 or the parts at the high-pressure turbine 1, that is: under the condition of high temperature or high temperature difference, parts are deformed due to the thermal vibration phenomenon generated by the high temperature or the local high temperature difference, and the safe operation of the gas turbine is influenced. In response to the situation, the domestic conventional practice is to redesign and change the structures of the high-pressure rotor 8 and the high-pressure turbine 1, or to select the parts from materials with strong deformation resistance under the condition of high temperature or high temperature difference; both conventional solutions may bring about mass increase, cost increase and other unknown uncertain problems, which will have a negative impact on the operational performance and reliability of the gas turbine.
Therefore, the present embodiment utilizes the existing structural features of the gas turbine to perform structural reinforcement, in the existing structure of the gas turbine, the high-pressure rotor 8 of the gas turbine has the labyrinth plate 5, the center of the labyrinth plate 5 itself is in a hole shape, and one end surface of the labyrinth plate 5 far away from the high-pressure rotor 8 is connected to the high-pressure turbine 1 through the drum shaft 3, and the turbine shaft 9 is connected in the high-pressure turbine 1.
The reinforcing structure used in this embodiment includes a joint shaft, an adjustment pad 7, and a bush 6.
The adapter shaft comprises a rotor side shaft body 4 and a turbine side shaft body 2, and the rotor side shaft body 4 is in butt joint with the turbine side shaft body 2. The two-section structural design of the rotor side shaft body 4 and the turbine side shaft body 2 can facilitate the processing of the transfer shaft, and avoid the problems of high processing difficulty, high rejection rate, high cost and the like of parts with longer length. In addition, because the temperature and temperature difference change born by different positions are different, and the requirements for the performances such as rigidity, hardness and the like and material selection are also different, the two-section design can better meet the requirements.
The rotor side shaft body 4 is integrally made of high-temperature-resistant powder alloy materials, and the characteristics of small thermal stress and small thermal bending deformation of the high-temperature powder alloy under the conditions of high temperature and high temperature difference are fully utilized. The rotor-side shaft body 4 includes a first support portion 41, a shaft body 42, a second support portion 43, a first mating portion 45, and the like.
The shaft body 42 of the rotor-side shaft body 4 is in a circular tube shape, and the shaft body 42 itself can play a role of transmitting a supporting force.
A first support portion 41 is provided at the left end of the shaft body 42, and this first support portion 41 is capable of fitting the connection bush 6, the first support portion 41 radially protruding from the outer peripheral wall of the rotor-side shaft body 4 and taking the shape of a disk. The transfer shaft can transmit axial supporting force to the left side of the transfer shaft through the first supporting part 41, so that the labyrinth plate 5 can be pressed tightly in the axial direction, and the deformation tendency generated by the thermal vibration phenomenon of the labyrinth plate 5 and parts at the high-pressure rotor 8 is inhibited. In addition, the thickness of the sidewall of the shaft body 42 on the left side of the first supporting portion 41 is increased, and the increased thickness portion can extend into the center of the grate plate 5 and provide a radial supporting force.
The second support portion 43 is provided at the right end of the shaft body 42, the rotor-side shaft body 4 having a bucket shape extending radially outward; the joint of the drum shaft 3 and the high-pressure turbine 1 is annular; the outer edge of the second support part 43 extends to the joint of the drum shaft 3 and the high-pressure turbine 1, so that the outer edge of the second support part 43 can be abutted against the inner side of the joint of the drum shaft 3 and the high-pressure turbine 1, and provides radial support force for the joint, when the temperature of the joint is high or the temperature difference change is large and the deformation trend is caused by the thermal vibration phenomenon, the deformation force of the joint can be effectively counteracted through the support of the second support part 43, and the joint is ensured not to be deformed by the thermal vibration.
A first butt joint portion 45 is located at the intersection of the second support portion 43 and the shaft body 42, the first butt joint portion 45 is used for butt joint of the turbine side shaft body 2, the first butt joint portion 45 is in an annular step shape, and one end of the turbine side shaft body 2, which is used for butt joint of the first butt joint portion 45, is provided with a corresponding second butt joint portion, and the second butt joint portion and the first butt joint portion 45 are in a plug-in fit structure, so that the turbine side shaft body 2 can be butt-jointed to the rotor side shaft body 4 in a plug-in mode.
The turbine side shaft body 2 is in a circular tube shape, the left end of the turbine side shaft body 2 is provided with a second butt joint part, the right end of the turbine side shaft body 2 abuts against the end face of the turbine shaft 9, the turbine side shaft body 2 provides radial supporting force for the high-pressure turbine 1, meanwhile, the supporting force of the turbine shaft 9 is transmitted to the rotor side shaft body 4, the axial supporting force on the turbine shaft 9 is transmitted to the grate disc 5, and therefore the deformation resistance of the parts where the high-pressure rotor 8 and the high-pressure turbine 1 are located in the thermal vibration phenomenon is improved.
When in use, the bushing 6 is sleeved on the first supporting part 41 at the left end of the transfer shaft, the whole bushing 6 is in a ring shape, the bushing 6 is also made of a high-temperature-resistant powder alloy material in an integrated forming mode, and the characteristics of low thermal stress and low thermal bending deformation of the high-temperature powder alloy under the conditions of high temperature and high temperature difference are utilized. The outer peripheral surface of the lining 6 is inclined, so that the lining can be embedded in the center of the grate plate 5, and the outer wall of the lining 6 can be positioned on the inner wall of the center of the grate plate 5, so as to assist in the alignment of the transfer shaft and the grate plate 5. The left end of the transfer shaft is abutted against the center of the grate plate 5 through the bush 6, and the bush 6 mainly plays roles of structural adaptation and supporting force transmission between the grate plate 5 and the transfer shaft.
An axial convex tooth 62 and a radial convex tooth 63 are arranged at the edge of the end face of one side of the bush 6. The axial convex teeth 62 project in the axial direction of the bush 6; the outer edge of the first supporting portion 41 is provided with a groove 44 corresponding to the axial convex tooth 62, and the axial convex tooth 62 provides a radially inward supporting force for the rotor-side shaft body 4. The axial teeth 62 of the arrangement in this embodiment can extend into the teeth on the first support 41 when in use, thereby providing radial inward supporting force for the first support 41, and avoiding the first support 41 from being damaged under the action of centrifugal force of high-speed rotation. The radial teeth 63 extend radially outwards and abut against the first support 41, so as to transmit force in the axial direction. In the scheme, the radial convex teeth 63 arranged on the lining 6 can transmit the supporting force of the rotor side shaft body 4 to the center of the grate disc 5, and meanwhile, the lining 6 also plays a role in connecting the grate disc 5 and the adapter shaft.
The adjusting pad 7 is arranged at the joint of the bushing 6 and the transfer shaft and transmits axial supporting force, and the adjusting pad 7 is made of titanium alloy materials. The titanium alloy adjusting pad 7 has excellent rigidity, so that the titanium alloy adjusting pad can effectively reinforce the thermal stress deformation of the front and rear parts and can effectively connect the front and rear parts. The adjusting pad 7 is circular and mainly plays a role in conducting axial supporting force.
The reinforcing structure comprises a transfer shaft, an adjusting pad 7, a lining 6 and other parts, axial supporting force can be transmitted to the high-pressure rotor 8 when the reinforcing structure is used, when the high-pressure rotor 8 deforms due to thermal vibration, the drum shaft 3 provides supporting force for correction, and meanwhile, the end of the transfer shaft transmits the axial supporting force to the center of the grate disc 5, so that the stability of the structure of the high-pressure rotor 8 is improved, and due to the fact that the supporting position of the transfer shaft is different from the connecting position of the drum shaft 3, a local lever effect is formed between the transfer shaft and the drum shaft, the connecting position of the grate disc 5 and the drum shaft 3 serves as a fulcrum, the support of the transfer shaft is utilized, and the problem that the deformation of the outer side of the grate disc and the deformation of the disc body of the grate disc exceed the standard due to the phenomenon of thermal vibration is solved.
Example 2
As shown in fig. 1 to 6, the coupling shaft has a hollow pipe sleeve shape in the structure of embodiment 1; a cavity is arranged between the transfer shaft and the drum shaft 3, the cavity is divided into a front chamber and a rear chamber by a second supporting part 43 arranged on the transfer shaft, and a through hole is arranged on the second supporting part 43 to communicate the two chambers. In the scheme, a hollow structure is arranged in the transfer shaft, and a cavity is formed between the transfer shaft and the drum shaft 3, so that the weight of the high-pressure rotor 8 and the high-pressure turbine 1 can be reduced, and air circulation and heat dissipation can be performed through the cavities.
The above examples are merely for clearly illustrating the examples and are not intended to limit the embodiments; and are neither required nor exhaustive of all embodiments. And obvious variations or modifications of this technology may be resorted to while remaining within the scope of the technology.
Claims (10)
1. The utility model provides a reinforcement structure that thermal vibration deformation was prevented to gas turbine high pressure rotor which characterized in that: comprises a transfer shaft, an adjusting pad (7) and a bushing (6);
a grate disc (5) is arranged on a high-pressure rotor (8) of the gas turbine, and the grate disc (5) is connected to the high-pressure turbine (1) through a drum shaft (3); a turbine shaft (9) is connected in the high-pressure turbine (1);
the bushing (6) is sleeved at one end of the transfer shaft; one end of the transfer shaft is abutted against the center of the grate disc (5) through the lining (6); the other end of the transfer shaft extends to the center of the high-pressure turbine (1) and is abutted against the turbine shaft (9); the adjusting pad (7) is arranged at the joint of the bushing (6) and the adapter shaft and transmits axial supporting force.
2. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 1, wherein: the adapter shaft comprises a rotor side shaft body (4) and a turbine side shaft body (2), and the rotor side shaft body (4) is in butt joint with the turbine side shaft body (2).
3. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 2, wherein: a second supporting part (43) extending outwards in the radial direction is arranged on the rotor side shaft body (4); the joint of the drum shaft (3) and the high-pressure turbine (1) is annular; the outer edge of the second supporting part (43) is abutted against the inner side of the joint of the drum shaft (3) and the high-pressure turbine (1).
4. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 2, wherein: the turbine side shaft body (2) abuts against the end face of the turbine shaft (9) and provides radial supporting force for the high-pressure turbine (1).
5. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 1, wherein: one end of the transfer shaft, which is connected with the bush (6), is provided with a first supporting part (41), and the first supporting part (41) radially protrudes from the peripheral wall of the rotor side shaft body (4) and is disc-shaped.
6. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 5, wherein: the axial convex teeth (62) are arranged at the edge of the end face of one side of the bushing (6), and the axial convex teeth (62) extend out along the axial direction of the bushing (6); the outer edge of the first supporting part (41) is provided with a groove (44) corresponding to the axial convex tooth (62), and the axial convex tooth (62) provides a radially inward supporting force for the rotor side shaft body (4).
7. The reinforcing structure of the high-pressure rotor of a gas turbine against thermal vibration deformation according to claim 5, characterized in that the edge of said bushing (6) is provided with radial convex teeth (63); the radial convex teeth (63) extend outwards in the radial direction and are abutted against the first supporting part (41) so as to transmit force in the axial direction.
8. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 5, wherein: the peripheral surface of the bush (6) is inclined, so that the bush can be embedded in the center of the grate plate (5).
9. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 1, wherein: the transfer shaft is in a hollow pipe sleeve shape; a cavity is arranged between the transfer shaft and the drum shaft (3), a second supporting part (43) arranged on the transfer shaft divides the cavity into a front cavity and a rear cavity, and a through hole is formed in the second supporting part (43) to communicate the two cavities.
10. The reinforcing structure for a high-pressure rotor of a gas turbine against thermal vibration deformation of claim 1, wherein: the bushing (6) and the adapter shaft are made of high-temperature-resistant powder alloy materials, and the adjusting pad (7) is made of titanium alloy materials.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114184390A (en) * | 2022-02-16 | 2022-03-15 | 成都中科翼能科技有限公司 | Gas turbine rotor axial force test sensor and parameter design method |
| CN116733613A (en) * | 2023-08-10 | 2023-09-12 | 成都中科翼能科技有限公司 | Transition section structure of gas turbine |
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| CN116733613B (en) * | 2023-08-10 | 2023-10-20 | 成都中科翼能科技有限公司 | Transition section structure of gas turbine |
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