CN114033744A - Novel gas turbine low-pressure compressor rotor structure and assembling method - Google Patents
Novel gas turbine low-pressure compressor rotor structure and assembling method Download PDFInfo
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- CN114033744A CN114033744A CN202210024697.0A CN202210024697A CN114033744A CN 114033744 A CN114033744 A CN 114033744A CN 202210024697 A CN202210024697 A CN 202210024697A CN 114033744 A CN114033744 A CN 114033744A
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
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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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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a novel rotor structure of a low-pressure compressor of a gas turbine and an assembly method, wherein the rotor structure comprises working impellers of one to six stages, and two adjacent stages of working impellers are connected with a distance ring assembly through a passage ring assembly; the working impeller of the first stage is connected with the front sealing labyrinth disc, and the working impeller of the sixth stage is connected with the rear sealing labyrinth disc; the distance ring group is connected with the working impeller through a bolt, and a locking nut is screwed on the bolt; the passage ring assembly is connected with the working impeller through a pin, a pin hole is formed between the passage ring assembly and the working impeller, and swing gaps are formed between the pin and the pin hole and between the passage ring assembly and the working impeller. The assembly method comprises the following steps: aligning all the parts in place; and (4) pre-tightening the locking nut on the bolt, unscrewing 2 circles after 20-30min, and finally tightening. The invention ensures the centering and the torque transmission among the components, and can realize good centering and reliable force transmission.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a novel rotor structure of a low-pressure compressor of a gas turbine and an assembly method.
Background
The compressor rotor is an assembly that rotates at high speed to work on the air flow. In the existing compressor rotor, under a high-speed condition, rotor parts and joints thereof bear huge inertia force and gas force. The existing drum rotors, the basic component of which is a cylindrical, olive or conical structure, connected with front and rear half-shafts by means of mounting edges and bolts, have poor centrifugal load capacity and can only be used at low peripheral speeds (not more than 180 and 200 m/s). Such as the low pressure rotor of the earlier compressor, modern high flow compressor turbofan engines. The rotors of the low-pressure compressor of the civil Sbei engine are all drum type rotors. The drum rotor has more parts, and the manufacturing deviation can influence the centering and the balance of the rotor, so that the quality in production cannot be controlled, which is a technical problem to be solved at present.
Disclosure of Invention
The invention aims to provide a novel rotor structure of a low-pressure compressor of a gas turbine and an assembling method, which are used for solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
on one hand, the invention provides a novel gas turbine low-pressure compressor rotor structure which comprises first-stage to sixth-stage working impellers, wherein the first-stage to sixth-stage working impellers are arranged on a rotating shaft of a low-pressure compressor and are sequentially arranged from the front end to the rear end of the low-pressure compressor; one end of the working impeller of the first stage, which is close to the front end of the low-pressure compressor, is connected with the front sealing labyrinth disc, and one end of the working impeller of the sixth stage, which is close to the rear end of the low-pressure compressor, is connected with the rear sealing labyrinth disc through a spacing ring assembly; each distance ring assembly is connected with the working impeller connected with the distance ring assembly through a bolt, and a locking nut is screwed on the bolt; each passage ring component is connected with the working impeller connected with the passage ring component through pins, pin holes are formed between the passage ring component corresponding to each pin and the working impeller in a matched mode, and swinging gaps allowing the working impeller to swing around the pins are formed between each pin and the corresponding pin hole and between each passage ring component and the working impeller connected with the passage ring component.
In the invention, as a preferable technical scheme, in the working impellers of two to six stages, the working impeller of each stage and two distance ring assemblies connected with the working impeller of each stage are connected through the same bolt.
As a preferred technical scheme in the invention, a front journal of the low-pressure compressor is arranged at the front end of the rotating shaft of the low-pressure compressor, and the working impeller of the second stage, the two distance ring assemblies connected with the working impeller of the second stage and the front journal of the low-pressure compressor are all connected through the same bolt.
As a preferred technical scheme, the front sealing labyrinth disc, the first-stage working impeller and the distance ring assembly connected with the first-stage working impeller are connected through the same bolt.
As a preferred technical scheme in the invention, a rear end of the rotating shaft of the low-pressure compressor is provided with a rear journal of the low-pressure compressor, and the fifth-stage working impeller, the two distance ring assemblies connected with the fifth-stage working impeller and the rear journal of the low-pressure compressor are all connected through the same bolt.
As a preferable technical scheme, the rear sealing labyrinth disc and the distance ring assembly connected with the rear sealing labyrinth disc are connected through a bolt, and a locking nut is screwed on the bolt.
In another aspect, the invention further provides an assembling method of a novel rotor structure of a low-pressure compressor of a gas turbine, which includes the following specific steps:
aligning a rotating shaft of the low-pressure compressor, first-stage to sixth-stage working impellers, all passage ring assemblies, all distance ring assemblies, a front sealing labyrinth disc, a rear sealing labyrinth disc, all bolts, all locking nuts and all pins in place according to installation positions before assembly;
during assembly, all the locking nuts are respectively pre-tightened on the corresponding bolts, and the torque during pre-tightening is (45 +/-3) N.m;
all the locking nuts are kept for 20-30min under a pre-tightening state, and then each locking nut is unscrewed for 2 circles;
and finally screwing the 2-turn loosened locknut, wherein the torque during screwing is (40 +/-3) N.m.
As a preferable technical scheme in the invention, after the locking nut is screwed down, the relative position of the five passage ring assemblies to the axis of the engine is detected, and the relative position of the five passage ring assemblies to the axis of the engine is ensured to be correct.
Has the advantages that: in the structural design of the invention, pins are used for connecting the working impeller and the passage ring component to transmit the load of the working impeller, and swinging gaps allowing the working impeller to swing around the pins are arranged between the pins and the pin holes as well as between the passage ring component connected with the pins and the working impeller, so that the invention has the functions of damping and eliminating the additional stress at the connecting part; meanwhile, the distance ring assembly, the passage ring assembly and the working impeller are connected layer by layer through the structural design, the balance and the transverse rigidity of the rotor are guaranteed, the front sealing labyrinth disc and the rear sealing labyrinth disc are indirectly connected with the working impeller through the front sealing labyrinth disc and the rear sealing labyrinth disc, the structure is fixed, bolts and locking nuts are selected in the structure and used for guaranteeing centering and torque transmission between connected parts, good centering and reliable force transmission can be achieved, the number of large parts is reduced through the structural scheme, and the detachability of the rotor is brought into full play. The front sealing labyrinth disc and the rear sealing labyrinth disc connecting structure device can ensure the quality control in production and improve the efficiency of the gas compressor by reducing the gas leakage loss.
Drawings
FIG. 1 is a schematic structural diagram of a first part of a rotor structure of a low-pressure compressor of a novel gas turbine according to the invention;
FIG. 2 is a second partial schematic structural view of a rotor structure of a low-pressure compressor of the novel gas turbine (the second partial schematic structural view is connected with the first partial schematic structural view);
FIG. 3 is a third partial schematic structural view of a rotor structure of a low-pressure compressor of the novel gas turbine (the third partial schematic structural view is connected with the second partial schematic structural view);
fig. 4 is a fourth part of the structure of the rotor of the low-pressure compressor of the novel gas turbine (the fourth part of the structure is connected with the third part of the structure);
fig. 5 is an enlarged schematic view of a portion a of fig. 1.
In the figure: 1-a working impeller; 2-a via ring assembly; 3-a distance ring assembly; 4-front sealing labyrinth plate; 5-rear sealing labyrinth plate; 6-bolt; 7-locking the nut; 8-pins; 9-front shaft neck of low-pressure compressor; 10-rear journal of low-pressure compressor.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the present invention will be briefly described below with reference to the accompanying drawings and the embodiments or the description in the prior art, it is obvious that the following description of the structure of the drawings is only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto.
The first embodiment is as follows:
as shown in fig. 1-5, the present embodiment provides a novel rotor structure of a low-pressure compressor of a gas turbine, which includes first to sixth stages of working impellers 1 installed on a rotating shaft of the low-pressure compressor and sequentially arranged from a front end to a rear end of the low-pressure compressor, and the working impellers 1 of each stage are connected into a whole by the rotating shaft of the low-pressure compressor and associated structures are connected into a whole.
The outer sides of any two adjacent stages of working impellers 1 are connected through a passage ring assembly 2, and the inner sides of any two adjacent stages of working impellers 1 are connected through a distance ring assembly 3, so that the two adjacent stages of working impellers 1 can be stably connected together, and the working impellers 1 of one stage to six stages are combined into a stable whole; one end of the first-stage working impeller 1 close to the front end of the low-pressure compressor is connected with a front sealing labyrinth disc 4, one end of the sixth-stage working impeller 1 close to the rear end of the low-pressure compressor is connected with a rear sealing labyrinth disc 5 through a distance ring assembly 3, and the front sealing labyrinth disc 4 and the rear sealing labyrinth disc 5 are connected to a rotating shaft of the low-pressure compressor, so that all the working impellers 1, the passage ring assemblies 2 and the distance ring assemblies 3 are positioned on the rotating shaft of the low-pressure compressor; each distance ring assembly 3 is connected with the working impeller 1 connected with the distance ring assembly through a bolt 6, a locking nut 7 is screwed on the bolt 6, and the distance ring assembly 3 is stably connected with the working impeller 1 through the matching of the bolt 6 and the locking nut 7; each passage ring component 2 is connected with the working impeller 1 connected with the passage ring component through a pin 8, so that the passage ring components 2 and the working impeller 1 are positioned, pin holes are formed between the passage ring components 2 corresponding to the pins 8 and the working impeller 1 in a matched mode, swinging gaps allowing the working impeller 1 to swing around the pins 8 are formed between each pin 8 and the corresponding pin hole and between each passage ring component 2 and the working impeller 1 connected with the passage ring component, the working impeller is allowed to swing around the pins during working, and the functions of damping and eliminating additional stress at the connecting part are achieved.
It should be noted that, because of the installation location of the pin 8, in practice, the pin hole on the working impeller 1 is located on the inner side of the working impeller 1, and there is a certain opening at the lower end of the pin hole on the working impeller 1, but the fit with the pin 8 and the passage ring assembly 2 is not affected.
The compressor rotor is an assembly which rotates at a high speed to work on airflow, and the rotating speed can reach thousands or tens of thousands of revolutions per minute, so that the rotor part and the connection part thereof bear the inertia force, the gas force, the torque and the complex vibration load of huge pressure.
In the structural design of the invention, the working impeller 1 and the passage ring component 2 are connected by using the pin 8 to transmit the load of the working impeller, and swinging gaps which allow the working impeller 1 to swing around the pin 8 are arranged between the pin 8 and a pin hole and between the passage ring component 2 connected with the pin 8 and the working impeller 1, so that the invention has the functions of damping and eliminating additional stress at the connection part; meanwhile, the distance ring assembly 3, the passage ring assembly 2 and the working impeller 1 are connected layer by layer through the structural design, the balance and the transverse rigidity of the rotor are guaranteed, the front sealing labyrinth disc 4 and the rear sealing labyrinth disc 5 are indirectly connected with the working impeller 1 through the front sealing labyrinth disc and the rear sealing labyrinth disc, the structure is more fixed, bolts 6 and locking nuts 7 are selected in the structure, the bolts 6 are connected with the locking nuts 7 to guarantee centering and torque transmission among connected parts, good centering and reliable force transmission can be achieved, the number of large parts is reduced through the structural scheme, and the detachability of the rotor is brought into full play. The connecting structure device of the front sealing labyrinth plate 4 and the rear sealing labyrinth plate 5 can ensure the quality control in production and improve the efficiency of the gas compressor by reducing the gas leakage loss.
As a preferred embodiment in this embodiment, it should be further described that, in the working impellers 1 of two to six stages, the working impeller 1 of each stage and the two distance ring assemblies 3 connected thereto are connected by the same bolt 6, and are connected by one bolt 6 to three components, and then are locked by the lock nut 7, on the basis of ensuring the structural stability, the use amount of the bolt 6 can be reduced, the cost can be saved, and the number of the threaded holes formed in the components can be reduced, so as to reduce the damage to the structure of the components as much as possible, ensure the structural integrity of the components, and ensure the service life of the whole.
As a preferred embodiment in this embodiment, it should be further described that the front end of the rotating shaft of the low-pressure compressor is provided with a front journal 9 of the low-pressure compressor, the second-stage working impeller 1, the two distance ring assemblies 3 connected to the second-stage working impeller 1, and the front journal 9 of the low-pressure compressor are all connected by the same bolt 6, and the four components are connected by one bolt 6 and then locked by a locking nut 7, on the basis of ensuring that the main component structure is stably matched with the rotating shaft of the low-pressure compressor, the usage amount of the bolt 6 can be reduced, the cost is saved, the number of threaded holes formed in the component can be reduced, the damage to the component structure can be reduced as much as possible, the structural integrity of the component can be ensured, and the service life of the whole can be ensured. Meanwhile, the structural design of the low-pressure compressor front journal 9 of the low-pressure compressor rotor structure in the embodiment can further enhance the pressing force at the disk edge during working, so that the centrifugal force of the low-pressure compressor front journal 9 can generate a forward pressing effect to tightly press the disk edge, thereby playing a role in enhancing the connection rigidity along with the increase of the rotating speed.
As a preferred embodiment in this embodiment, it should be further described that the front sealing labyrinth disc 4, the first-stage working impeller 1, and the distance ring assembly 3 connected to the first-stage working impeller 1 are connected by the same bolt 6, and are connected by one bolt 6 to four components, and then are locked by the lock nut 7, on the basis of ensuring that the main component structure is stably matched with the low-pressure compressor rotating shaft, the use amount of the bolt 6 can be reduced, the cost is saved, the number of the threaded holes formed in the components can be reduced, the damage to the component structure can be reduced as much as possible, the structural integrity of the components can be ensured, and the service life of the whole can be ensured.
As a preferred embodiment in this embodiment, it should be further described that the rear end of the rotating shaft of the low-pressure compressor is provided with a rear journal 10 of the low-pressure compressor, the fifth-stage working impeller 1, the two distance ring assemblies 3 connected to the fifth-stage working impeller 1, and the rear journal 10 of the low-pressure compressor are all connected by the same bolt 6, and the four components are connected by one bolt 6 and then locked by a locking nut 7, on the basis of ensuring that the main component structure is stably matched with the rotating shaft of the low-pressure compressor, the usage amount of the bolt 6 can be reduced, the cost can be saved, the number of the threaded holes formed in the components can be reduced, the damage to the component structure can be reduced as much as possible, the structural integrity of the components can be ensured, and the service life of the whole can be ensured. Meanwhile, the structural design of the low-pressure compressor rear journal 10 of the low-pressure compressor rotor structure in the embodiment can further enhance the pressing force at the disk edge during working, so that the centrifugal force of the low-pressure compressor rear journal 10 can generate a forward pressing effect to tightly press the disk edge, thereby enhancing the connection rigidity along with the increase of the rotating speed.
As a preferred embodiment in this embodiment, it should be further explained that the rear sealing labyrinth disc 5 and the distance ring assembly 3 connected thereto are connected by a bolt 6, and a lock nut 7 is screwed on the bolt 6, so that the stability between the rear sealing labyrinth disc 5 and the distance ring assembly 3 connected thereto is enhanced by a bolt 6, that is, the stability of the distance ring assembly 3 connected to the rear sealing labyrinth disc 5 on the rotating shaft of the low-pressure compressor is enhanced, and the stability of other parts connected to the distance ring assembly 3 on the rotating shaft of the low-pressure compressor is enhanced at the same time.
Example two:
the embodiment provides an assembling method of a novel rotor structure of a low-pressure compressor of a gas turbine, which comprises the following specific steps:
before assembly, aligning a rotating shaft of the low-pressure compressor, a first-stage to sixth-stage working impeller 1, all passage ring assemblies 2, all distance ring assemblies 3, a front sealing labyrinth disc 4, a rear sealing labyrinth disc 5, all bolts 6, all locking nuts 7 and all pins 8 in place according to installation positions;
when the low-pressure gas compressor is assembled in place, the jumping amount is ensured by twisting the angular positions of the working impeller 1, the passage ring assembly 2, the distance ring assembly 3, the front sealing labyrinth 4, the rear sealing labyrinth 5, the front journal 9 of the low-pressure gas compressor and the rear journal 10 of the low-pressure gas compressor.
During assembly, all the locking nuts 7 are respectively pre-tightened on the corresponding bolts 6 according to the installation sequence, and the torque during pre-tightening is (45 +/-3) N.m;
all the locking nuts 7 are kept for 20-30min in a pre-tightening state, and then each locking nut 7 is unscrewed for 2 circles;
the 2-turn loosened lock nut 7 is finally tightened with a torque of (40 ± 3) N · m.
The existing torque wrench is adopted when each locking nut 7 is pre-tightened, unscrewed and finally screwed, so that the operation is convenient and the control is convenient.
In the present assembly method, since a false moment may actually occur, the two surfaces actually tightened are not in full contact, and therefore must be pre-tightened, then loosened, and then tightened again to ensure a tight face-to-face connection. The tension force of the bolt during assembly is called pretightening force, for the same rotor, when the working condition is unchanged, the pretightening force marks the degree of compression on the pressing surface between the rotor stages, the pretightening force is too small to ensure reliable work, and the pretightening force is too large, so that the tension stress in the bolt is too large and even broken, and therefore, the pretightening force is an important original parameter in the structural design of the rotor. When the structure works, the tension force of the bolt and the pressing force between stages are changed, the pretightening force of the structure bolt ensures the rigidity of the rotor, namely, the joint surface of the rotor is not opened under the action of bending moment, and secondly, the reliable torque in working is ensured in a structure of transmitting torque by using end face friction force. The rigidity of the rotor is guaranteed by the pretightening force of the bolts, and meanwhile, the bolts are used for guaranteeing centering and transmitting torque.
As a preferred embodiment in this embodiment, it should be further explained that after the locking nut 7 is tightened, the relative positions of the five passage ring assemblies 2 to the engine axis are detected, so as to ensure that the relative positions of the five passage ring assemblies 2 to the engine axis are correct, ensure the accuracy of the equipment, and if the positions are not within the industry standard range, the equipment is reassembled.
Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A novel gas turbine low-pressure compressor rotor structure comprises first to sixth working impellers (1) which are arranged on a low-pressure compressor rotating shaft and are sequentially arranged from the front end to the rear end of the low-pressure compressor, the outer sides of any two adjacent working impellers (1) are connected through a passage ring assembly (2), and the inner sides of any two adjacent working impellers (1) are connected through a distance ring assembly (3); one end of the working impeller (1) of the first stage, which is close to the front end of the low-pressure compressor, is connected with a front sealing labyrinth disc (4), and one end of the working impeller (1) of the sixth stage, which is close to the rear end of the low-pressure compressor, is connected with a rear sealing labyrinth disc (5) through a distance ring assembly (3); the device is characterized in that each distance ring assembly (3) is connected with the working impeller (1) connected with the distance ring assembly through a bolt (6), and a locking nut (7) is screwed on the bolt (6); each passage ring component (2) is connected with the working impeller (1) connected with the passage ring component through a pin (8), pin holes are formed between the passage ring component (2) corresponding to each pin (8) and the working impeller (1) in a matched mode, and swinging gaps allowing the working impeller (1) to swing around the pins (8) are formed between each pin (8) and the corresponding pin hole and between each passage ring component (2) and the working impeller (1) connected with the passage ring component.
2. The new gas turbine low-pressure compressor rotor structure as claimed in claim 1, characterized in that, in the working impellers (1) of two to six stages, the working impeller (1) of each stage and the two distance ring assemblies (3) connected with it are connected by the same bolt (6).
3. The novel gas turbine low-pressure compressor rotor structure as claimed in claim 1, wherein the front end of the low-pressure compressor rotating shaft is provided with a low-pressure compressor front journal (9), and the second-stage working impeller (1), the two distance ring assemblies (3) connected with the second-stage working impeller (1) and the low-pressure compressor front journal (9) are all connected through the same bolt (6).
4. The novel gas turbine low-pressure compressor rotor structure as claimed in claim 1, wherein the front sealing labyrinth disc (4), the first stage working impeller (1) and the distance ring assembly (3) connected with the first stage working impeller (1) are connected through the same bolt (6).
5. The novel gas turbine low-pressure compressor rotor structure as claimed in claim 1, wherein the rear end of the low-pressure compressor rotating shaft is provided with a low-pressure compressor rear journal (10), and the fifth-stage working impeller (1), the two distance ring assemblies (3) connected with the fifth-stage working impeller (1) and the low-pressure compressor rear journal (10) are all connected through the same bolt (6).
6. The novel gas turbine low-pressure compressor rotor structure as claimed in claim 1, wherein the rear sealing labyrinth disc (5) and the distance ring assembly (3) connected with the rear sealing labyrinth disc are connected through a bolt (6), and a locking nut (7) is screwed on the bolt (6).
7. A novel assembling method for a rotor structure of a low-pressure compressor of a gas turbine is characterized by comprising the following specific steps of:
before assembly, aligning a rotating shaft of the low-pressure compressor, a first-stage to sixth-stage working impeller (1), all passage ring assemblies (2), all distance ring assemblies (3), a front sealing labyrinth disc (4), a rear sealing labyrinth disc (5), all bolts (6), all locking nuts (7) and all pins (8) in place according to installation positions;
during assembly, all the locking nuts (7) are respectively pre-tightened on the corresponding bolts (6), and the torque during pre-tightening is (45 +/-3) N.m;
all the locking nuts (7) are kept for 20-30min in a pre-tightening state, and then each locking nut (7) is unscrewed for 2 circles;
and finally screwing the 2-turn unscrewed lock nut (7), wherein the torque during screwing is (40 +/-3) N.m.
8. An assembly method according to claim 7, characterised in that after tightening of the locking nut (7), the relative position of the five passage ring assemblies (2) to the engine axis is checked to ensure that the relative positions of the five passage ring assemblies (2) to the engine axis are correct.
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| CN114687861A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Locking connection device of gas turbine low-pressure rotor |
| CN115789112A (en) * | 2023-02-09 | 2023-03-14 | 中国航发四川燃气涡轮研究院 | Connecting structure for mounting remote measuring device of aircraft engine |
| CN115816071A (en) * | 2023-02-07 | 2023-03-21 | 成都中科翼能科技有限公司 | Assembly method of gas turbine supporting structure |
| CN117345433A (en) * | 2023-12-06 | 2024-01-05 | 成都中科翼能科技有限公司 | Sealing assembly component of gas turbine exhaust casing |
| CN117697692A (en) * | 2024-02-06 | 2024-03-15 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
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| CN114687861A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Locking connection device of gas turbine low-pressure rotor |
| CN115816071A (en) * | 2023-02-07 | 2023-03-21 | 成都中科翼能科技有限公司 | Assembly method of gas turbine supporting structure |
| CN115816071B (en) * | 2023-02-07 | 2023-04-28 | 成都中科翼能科技有限公司 | Assembling method of gas turbine supporting structure |
| CN115789112A (en) * | 2023-02-09 | 2023-03-14 | 中国航发四川燃气涡轮研究院 | Connecting structure for mounting remote measuring device of aircraft engine |
| CN117345433A (en) * | 2023-12-06 | 2024-01-05 | 成都中科翼能科技有限公司 | Sealing assembly component of gas turbine exhaust casing |
| CN117345433B (en) * | 2023-12-06 | 2024-02-06 | 成都中科翼能科技有限公司 | Sealing assembly component of gas turbine exhaust casing |
| CN117697692A (en) * | 2024-02-06 | 2024-03-15 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
| CN117697692B (en) * | 2024-02-06 | 2024-04-23 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
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