CN118346391A - Aviation turboshaft engine easy to maintain - Google Patents
Aviation turboshaft engine easy to maintain Download PDFInfo
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- CN118346391A CN118346391A CN202410722300.4A CN202410722300A CN118346391A CN 118346391 A CN118346391 A CN 118346391A CN 202410722300 A CN202410722300 A CN 202410722300A CN 118346391 A CN118346391 A CN 118346391A
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- 238000009434 installation Methods 0.000 claims abstract description 25
- 238000012546 transfer Methods 0.000 claims abstract description 24
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 8
- 230000013011 mating Effects 0.000 description 3
- 230000004323 axial length Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000011109 contamination Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Abstract
The application discloses an easily maintained aviation vortex shaft engine which comprises a turbine rotor unit body, an adapter shaft and a turbine shaft unit body. The turbine rotor unit body has a first axially extending mounting channel. The transfer shaft is coaxially arranged in a first mounting channel of the turbine rotor unit body, the turbine rotor unit body can be sleeved on the transfer shaft or moved out of the transfer shaft, the transfer shaft is fixedly connected with the turbine rotor unit body so as to limit the relative movement of the turbine rotor unit body and the transfer shaft, and the transfer shaft is provided with a second mounting channel coaxial with the first mounting channel; the turbine shaft unit body comprises a power turbine shaft, one end of the power turbine shaft is coaxially arranged in the second installation channel, the power turbine shaft can be inserted into or removed from the switching shaft, and the switching shaft is fixedly connected with the power turbine shaft so as to limit the relative movement of the switching shaft and the power turbine shaft. The aviation scroll engine easy to maintain can reduce the assembly difficulty and improve the assembly efficiency.
Description
Technical Field
The invention relates to the technical field of aviation equipment, in particular to an aviation scroll engine easy to maintain.
Background
The prior turboshaft engine is designed into a unit body for improving maintainability, wherein the unit body comprises a power turbine rotor unit body and a power turbine shaft unit body. The power turbine shaft unit body comprises a power turbine shaft, and the power turbine shaft is connected with the power turbine rotor unit body through interference fit or welding. In the use, when the power turbine rotor unit body or the power turbine shaft unit body is damaged, the whole power turbine rotor unit body or the power turbine shaft unit body is required to be sent into an internal site for replacement, equipment and personnel requirements on a replacement site are high, and the replacement efficiency is low.
Disclosure of Invention
The invention provides an aviation scroll engine easy to maintain, which aims to solve the technical problem that parts of the aviation engine are difficult to replace.
According to one aspect of the present invention, there is provided an aero-scroll engine for easy maintenance, the aero-scroll engine comprising:
A turbine rotor unit body having a first axially extending mounting channel;
The turbine rotor unit body is fixedly connected with the turbine rotor unit body so as to limit the relative movement of the turbine rotor unit body and the turbine rotor unit body, and the turbine rotor unit body is provided with a first installation channel coaxial with the first installation channel;
The turbine shaft unit body comprises a power turbine shaft, one end of the power turbine shaft is coaxially arranged in the second installation channel, the power turbine shaft can be inserted into the switching shaft along the second direction or removed from the switching shaft along the first direction, the switching shaft is fixedly connected with the power turbine shaft to limit the relative movement of the switching shaft and the power turbine shaft, and the rotation of the turbine rotor unit body can be transmitted to the turbine shaft unit body through the switching shaft;
the power turbine shaft is axially arranged, a first step surface is arranged on the power turbine shaft, and a second step surface axially opposite to the first step surface is arranged on the switching shaft; the turbine shaft unit body comprises a first adjusting piece, the first adjusting piece is sleeved on the turbine shaft unit body along a first direction, the first end face of the first adjusting piece is abutted to a first step face of the power turbine shaft, and the second end face of the first adjusting piece is abutted to a second step face of the switching shaft;
The aviation turboshaft engine comprises a front casing which is positioned at one end of the power turbine shaft far away from the turbine rotor unit body; the turbine shaft unit body comprises a front supporting seat and a front bearing, the front supporting seat is fixedly connected with the front casing, the front bearing is arranged on the front supporting seat, and one end of the power turbine shaft penetrates through the front bearing to be connected with the front supporting seat in a rotating mode.
In some embodiments, the first adjusting member includes a first adjusting ring and a second adjusting ring disposed in sequence along the second direction and abutting each other.
In some embodiments, the front support seat has a mounting end face matching the front casing, the first adjusting ring has a ring end face abutting the second adjusting ring, and the first adjusting ring is used for enabling the axial dimension between the mounting end face and the ring end face to be a preset value.
In some embodiments, the turbine rotor unit body comprises a first-stage rotor, a second-stage guide and a second-stage rotor which are sequentially arranged along the axial direction, the aviation turboshaft engine comprises a first-stage guide arranged on one side, away from the second-stage guide, of the first-stage rotor in the axial direction, and the second adjusting ring is used for adjusting a gap between the first-stage guide and the first-stage rotor.
In some embodiments, the outer peripheral wall of the power turbine shaft has at least two mounting shaft surfaces sequentially arranged along the second direction and having sequentially reduced diameters, and the inner annular wall of the transfer shaft has at least two transfer inner annular surfaces sequentially arranged along the second direction and having sequentially increased diameters, and each mounting shaft surface is matched with the corresponding transfer inner annular surface.
In some embodiments, the turbine rotor unit body comprises a primary rotor, a secondary guide and a secondary rotor which are sequentially arranged along the axial direction, and the aviation scroll engine further comprises a rear casing positioned at one side of the secondary guide radially outwards;
the turbine rotor unit body comprises a second adjusting piece, and the second adjusting piece is axially positioned between the rear casing and the secondary guide, so that the axial position of the secondary guide between the primary rotor and the secondary rotor is adjusted.
In some embodiments, one of the adapter shaft and the power turbine shaft has a keyway, the other has a connecting key, and the cooperation of the connecting key and the keyway limits the relative rotation of the adapter shaft and the power turbine shaft;
the aviation turboshaft engine comprises a first fastener, wherein the first fastener is in threaded connection with one end of the power turbine shaft, which is connected with the switching shaft, and is abutted to the switching shaft so as to fix the axial position of the switching shaft.
In some embodiments, the aviation turboshaft engine comprises a rear support seat and a rear bearing, the rear bearing is arranged on the rear support seat, and the adapter shaft is arranged on the rear bearing in a penetrating manner so as to be rotationally connected with the rear support seat.
The invention has the following beneficial effects: the turbine rotor unit body is provided with a first installation channel extending in the axial direction, the transfer shaft is coaxially arranged in the first installation channel of the turbine rotor unit body, one end of the power turbine shaft of the turbine shaft unit body is coaxially arranged in the second installation channel, so that the coaxial arrangement of the turbine rotor unit body and the turbine shaft unit body is realized, the transfer shaft is fixedly connected with the turbine rotor unit body through the fastening connection of the transfer shaft and the turbine shaft, and the rotation of the turbine rotor unit body can be transmitted to the turbine shaft unit body through the transfer shaft. When the turbine shaft unit body needs to be replaced, the fastening connection of the power turbine shaft and the switching shaft can be released, the turbine shaft unit body is pulled out of the second installation channel of the switching shaft, and then a new turbine shaft unit body penetrates into the second installation channel and is fastened, so that the replacement of the turbine shaft unit body is realized. When the turbine rotor unit body needs to be replaced, the turbine rotor unit body can be removed from being connected with the adapter shaft in a fastening mode, the turbine shaft unit body is automatically pulled out of the second installation channel of the adapter shaft, and then a new turbine shaft unit body penetrates into the second installation channel and is fastened, so that the replacement of the turbine rotor unit body is achieved. In addition, when the power turbine shaft is replaced, because the axial dimensions of the newly replaced power turbine shaft and the damaged power turbine shaft are different, the axial overall dimensions of the newly replaced power turbine shaft and the first adjusting piece along the axial direction meet the preset dimensions by arranging the matched first adjusting piece on the newly replaced power turbine shaft, and the axial compensation of the newly replaced power turbine shaft can be realized, so that the assembly requirement is met.
It can be understood that the adapter shaft, the power turbine shaft and the turbine rotor unit body are all in a fastening connection mode, so that the disassembly and assembly are relatively simple, and the disassembly efficiency is improved. In addition, the arrangement of the adapter shaft enables the turbine rotor unit body or the turbine shaft unit body to be detached independently, and disturbance to the other undetached component is avoided.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic view of a partial structure of an aero-scroll engine according to a preferred embodiment of the present invention;
FIG. 2 is a schematic view of the structure of a turbine rotor unit body and a power turbine shaft of a preferred embodiment of the present invention;
Fig. 3 is a schematic structural view of a turbine shaft unit body according to a preferred embodiment of the present invention.
Legend description:
10. a turbine rotor unit body; 10a, a first mounting channel;
20. a transfer shaft; 20a, a second mounting channel; 20b, a second step surface;
30. A turbine shaft unit body; 31. a power turbine shaft; 31a, a first step surface; 32. a first adjustment member; 321. a first adjustment ring; 322. a second adjustment ring; 33. a front support base; 34. a front bearing; 35. a primary rotor; 36. a secondary guide; 37. a secondary rotor; 38. a second adjustment member;
40. A front casing;
50. A rear case;
60. A fastener;
71. a rear support base; 72. a rear bearing;
80. a primary guide.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.
As shown in fig. 1, an aviation scroll engine with easy maintenance of this embodiment includes a turbine rotor unit 10, an adapter shaft 20, and a turbine shaft unit 30.
Referring to fig. 1 to 3, the turbine rotor unit body 10 has a first mounting passage 10a extending axially. In which the axial direction is the axial direction of the turbine rotor unit body 10, that is, the axial direction of the aviation scroll engine, or the axial direction of the turbine shaft unit body 30.
In some embodiments, the turbine rotor unit 10 includes a primary rotor 35, a secondary guide 36, a secondary rotor 37, and a sealing assembly, wherein the primary rotor 35, the secondary rotor 37 are driven to rotate by the high temperature air flow to provide power for rotation of the power turbine shaft 31 of the turbine shaft unit 30, the secondary guide 36 is located between the primary rotor 35 and the secondary rotor 37, the secondary guide 36 is capable of adjusting the direction of the high temperature air flow to the secondary rotor 37, and the sealing assembly is used for limiting the high temperature air flow to the radially inner side of the turbine rotor unit 10.
The adapter shaft 20 is coaxially disposed within the first mounting channel 10a of the turbine rotor unit body 10. The turbine rotor unit 10 can be sleeved on the adaptor shaft 20 along a first direction or moved out of the adaptor shaft 20 along a second direction, and the first direction is opposite to the second direction. In fig. 1, the first direction is an axial direction toward the left, and the second direction is an axial direction toward the right. When the turbine rotor unit 10 is replaced, the turbine rotor unit 10 is a moving object.
The adapter shaft 20 is fixedly connected with the turbine rotor unit body 10 to restrict relative movement of the two. It will be appreciated that when the adaptor shaft 20 is fastened to the turbine rotor unit body 10, the adaptor shaft 20 and the turbine rotor unit body 10 cannot move relative to each other, that is, when the adaptor shaft 20 is detached, the fastening connection between the adaptor shaft 20 and the turbine rotor unit body 10 needs to be released.
The adapter shaft 20 has a second mounting channel 20a coaxial with the first mounting channel 10 a.
The turbine shaft unit body 30 includes a power turbine shaft 31, and one end of the power turbine shaft 31 is coaxially disposed within the second mounting passage 20 a. In this way, the power turbine shaft 31 is coaxial with the adaptor shaft 20. Further, the power turbine shaft 31 is coaxial with the turbine rotor unit body 10.
The power turbine shaft 31 can be inserted into the adaptor shaft 20 in the second direction or removed from the adaptor shaft 20 in the first direction. It should be emphasized that the direction in which the power turbine shaft 31 is inserted into the adaptor shaft 20 is the second direction, and the direction in which the turbine rotor unit body 10 is sleeved on the adaptor shaft 20 is the first direction. The installation directions of the two are opposite, so that the separation action of the two can be conveniently realized.
The adaptor shaft 20 is fixedly coupled with the power turbine shaft 31 to restrict relative movement thereof, and rotation of the turbine rotor unit body 10 can be transmitted to the turbine shaft unit body 30 through the adaptor shaft 20. Specifically, the turbine rotor unit 10 is fastened to the adaptor shaft 20, and the adaptor shaft 20 is fastened to the power turbine shaft 31, so that the rotation of the turbine rotor unit 10 can be transmitted to the power turbine shaft 31 through the adaptor shaft 20, thereby driving the power turbine shaft 31 to rotate.
In the above embodiment, the turbine rotor unit 10 has the first mounting channel 10a extending in the axial direction, the adapter shaft 20 is coaxially disposed in the first mounting channel 10a of the turbine rotor unit 10, and one end of the power turbine shaft 31 of the turbine shaft unit 30 is coaxially disposed in the second mounting channel 20a, so that the coaxial arrangement of the turbine rotor unit 10 and the turbine shaft unit 30 is achieved, and the rotation of the turbine rotor unit 10 can be transmitted to the turbine shaft unit 30 through the adapter shaft 20 by fastening the adapter shaft 20 to the turbine rotor unit 10 and fastening the adapter shaft 20 to the power turbine shaft 31.
When the turbine shaft unit 30 needs to be replaced, the fastening connection of the power turbine shaft 31 and the adaptor shaft 20 can be released, the turbine shaft unit 30 is pulled away from the second installation channel 20a of the adaptor shaft 20 from the first direction, and then a new turbine shaft unit 30 is penetrated into the second installation channel 20a along the second direction and fastened, so that the replacement of the turbine shaft unit 30 is realized.
When the turbine rotor unit 10 needs to be replaced, the turbine rotor unit 10 and the adapter shaft 20 are fastened and connected, the turbine shaft unit 30 is pulled away from the second installation channel 20a of the adapter shaft 20 along the second direction, and then a new turbine shaft unit 30 is penetrated into the second installation channel 20a along the first direction and fastened, so that the turbine rotor unit 10 is replaced.
It can be understood that the adaptor shaft 20, the power turbine shaft 31 and the turbine rotor unit body 10 are all fastened and connected, so that the disassembly and assembly are relatively simple, and the disassembly efficiency is improved. In addition, when the turbine rotor unit body 10 or the turbine shaft unit body 30 is independently disassembled due to the arrangement of the adapter shaft 20, the undetached other part cannot be disturbed, and meanwhile, the direction of replacing the turbine shaft unit body 30 is opposite to the direction of replacing the turbine rotor unit body 10, so that structural interference between the turbine shaft unit body 30 and the turbine rotor unit body 10 in the replacing process is avoided, and the replacing difficulty is effectively reduced.
In some embodiments, the first mounting channel 10a is partially formed at least at the secondary rotor 37.
In some embodiments, the power turbine shaft 31 has a first stepped surface 31a thereon and the adaptor shaft 20 has a second stepped surface 20b axially opposite the first stepped surface 31a thereon. That is, the projections of the first step surface 31a and the second step surface 20b at least partially overlap in the axial direction.
The turbine shaft unit 30 includes a first adjuster 32, and the first adjuster 32 can be sleeved on the turbine shaft unit 30 along a first direction. The first end surface of the first adjusting member 32 axially abuts against the first step surface 31a of the power turbine shaft 31, and the second end surface of the first adjusting member 32 axially abuts against the second step surface 20b of the adaptor shaft 20.
Thus, when the power turbine shaft 31 is replaced, because the axial dimensions of the newly replaced power turbine shaft 31 and the damaged power turbine shaft 31 are different, the axial compensation of the newly replaced power turbine shaft 31 can be realized by arranging the matched first adjusting piece 32 on the newly replaced power turbine shaft 31, so that the overall dimension of the newly replaced power turbine shaft 31 and the first adjusting piece 32 along the axial direction meets the preset dimension, and the assembly requirement is met.
In some embodiments, the first adjuster 32 comprises a first adjuster ring. In this embodiment, the first adjustment ring and the corresponding mating power turbine shaft 31 are required to meet a predetermined size. That is, the disassembled first adjusting ring and the corresponding matched power turbine shaft 31 satisfy a preset size, and the first adjusting ring to be installed and the corresponding matched power turbine shaft 31 also satisfy the preset size. Thereby ensuring consistency in the mounting position of the power turbine shaft 31. That is, the first adjusting ring to be installed needs to be selected or ground to satisfy that the first adjusting ring to be installed and the corresponding matched power turbine shaft 31 also satisfy the preset size.
When the first turbine shaft needs to be replaced, the first adjusting ring can be predetermined before assembly according to the preset size and the power turbine shaft 31 to be assembled, so that the subsequent assembly difficulty is reduced.
In some embodiments, the aviation scroll engine includes a front casing 40 at an end of the power turbine shaft 31 remote from the turbine rotor unit body 10. The turbine shaft unit body 30 includes a front support seat 33 and a front bearing 34. The front support seat 33 has an installation end surface, the installation end surface of the front support seat 33 axially abuts against the front casing 40, and then the front support seat 33 and the front casing 40 are fastened and connected. The front bearing 34 is disposed on the front support base 33, and one end of the power turbine shaft 31 is disposed in the front bearing 34 in a penetrating manner so as to be rotatably connected with the front support base 33. The radial position of the power turbine shaft 31 is limited by the front bearing 34, so that the coaxiality of the power turbine shaft 31 and the front bearing 34 is ensured, and the installation accuracy is improved.
In this example, the preset dimension is an axial dimension between the mounting end face of the front support seat 33 and the second end face of the first adjuster 32.
When the detached turbine shaft unit 30 is repaired and replaced to another aviation scroll engine, the axial length of the other aviation scroll engine may be different from that of the original aviation scroll engine, so that the axial length needs to be compensated to ensure the relative consistency with the installation position of the power turbine rotor unit 10.
In some embodiments, the first adjuster 32 includes a first adjusting ring 321 and a second adjusting ring 322 that are disposed in order along the second direction and abut each other.
Further, in some embodiments, the front support seat 33 has a mounting end surface matching with the front casing 40, the first adjusting ring 321 has a ring end surface abutting against the second adjusting ring 322, and the first adjusting ring 321 is used to make the axial dimension between the mounting end surface and the ring end surface be a preset value.
It is understood that the first adjusting ring 321 is used to make the axial dimension between the mounting end surface and the ring end surface be a preset value, that is, the overall dimension of the first adjusting ring 321 and the power turbine shaft 31 meets the preset dimension. The first adjusting ring 321 and the power turbine shaft 31 are integrally sized to meet a preset value by replacing the first adjusting ring 321 with a different size or grinding the first adjusting ring 321.
Further, in some embodiments, the turbine rotor unit 10 includes a primary rotor 35, a secondary guide 36, and a secondary rotor 37 sequentially disposed along an axial direction, the aviation scroll engine includes a primary guide 80 disposed on a side of the primary rotor 35 axially facing away from the secondary guide 36, and the second adjusting ring is used to adjust a gap between the primary guide 80 and the primary rotor 35.
It will be appreciated that the primary guide 80 is fixed relative to the rear casing 50 during replacement of the turbine rotor unit body 10. When the detached turbine shaft unit body 30 is repaired and replaced to other aviation turboshaft engines, the gap size between the primary guide 80 and the primary rotor 35 can be controlled by adjusting the axial width size of the second adjusting ring 322. That is, the gap between the primary guide 80 and the primary rotor 35 is made to satisfy a preset size requirement by replacing the second adjustment ring 322 with a different size or grinding the second adjustment ring 322. It should be further added that when only the power turbine shaft 31 of the original aviation turboshaft engine is replaced, the gap between the primary guide 80 and the primary rotor 35 is unchanged, so that the second adjusting ring 322 does not need to be replaced, and only the first adjusting ring 321 needs to be replaced to meet the preset value.
In some embodiments, the outer peripheral wall of the power turbine shaft 31 has at least two mounting shaft faces that are disposed in sequence in the second direction and that decrease in diameter in sequence. It is understood that the two mounting axial surfaces are two mounting annular surfaces with coincident axial leads. It will be appreciated that the first step surface 31a may be formed at the location where the two mounting shaft surfaces meet.
The inner annular wall of the adapter shaft 20 is provided with at least two adapter inner annular surfaces which are sequentially arranged along the second direction and have sequentially increased diameters, and each installation shaft surface is matched with the corresponding adapter inner annular surface.
In this way, each mounting surface of the power turbine shaft 31 can be coaxially defined by the corresponding mating inner annular surface on the mating shaft 20, thereby further improving the coaxiality after mounting.
It can be appreciated that the end of the power turbine shaft 31 matching the adaptor shaft 20 presents a stepped diameter-reducing structure along the second direction, so as to facilitate the power turbine shaft 31 to be pulled away from the adaptor shaft 20 along the first direction while realizing concentricity limitation of a plurality of annular surfaces with different diameters.
In some embodiments, the aviation scroll engine includes a primary rotor 35, a secondary director 36, a secondary rotor 37 arranged in axial sequence, and an aft casing 50 located radially outward of the secondary director 36.
The turbine rotor unit body 10 includes a second adjuster 38, the second adjuster 38 being axially located between the rear casing 50 and the secondary guide 36, thereby adjusting the axial position of the secondary guide 36 between the primary rotor 35 and the secondary rotor 37.
It is understood that the second adjustment member 38 may be an adjustment ring structure. The inner annular surface of the rear casing 50 has a radially inwardly protruding stopper ring portion, and one end of the second adjuster 38 abuts against the stopper ring portion and the other end abuts against the secondary guide 36 to position the secondary guide 36.
It will be appreciated that by adjusting the axial width dimension of the first adjustment member 32, control of the axial position of the secondary guide 36 between the primary and secondary rotors 35, 37 can be achieved in a relatively simple manner with lower operator demands.
It is understood that the fastening connection includes circular arc end teeth + bolts, splines + nuts, spigots + bolts.
In some embodiments, the aviation scroll engine includes a first fastener 60, the first fastener 60 being threadably connected to one end of the power turbine shaft 31 that is connected to the adapter shaft 20 and abutting the adapter shaft 20 to fix the axial position of the adapter shaft 20. It can be appreciated that the first fastener 60 is convenient to assemble and disassemble, and can also play a role in limiting the axial position of the adapter shaft 20 while fixing the adapter shaft 20, thereby improving the assembly efficiency.
It will be appreciated that the end of the power turbine shaft 31 connected to the adaptor shaft 20 has threads, and the first fastener 60 may be in a nut structure, and is in threaded engagement with the power turbine shaft 31 to screw the adaptor shaft 20. When the first adjuster 32 is provided on the power turbine shaft 31, the axial position of the adapter shaft 20 is limited between the first fastener 60 and the first adjuster 32.
To further limit the relative rotation of the adaptor shaft 20 and the power turbine shaft 31, in some embodiments, one of the adaptor shaft 20 and the power turbine shaft 31 has a keyway, and the other has a connecting key, the cooperation of the connecting key and the keyway limiting the relative rotation of the adaptor shaft and the power turbine shaft 31.
Specifically, according to design requirements, a radially inwardly protruding connection key may be formed on the adapter shaft 20, and correspondingly, a key groove may be formed on the power turbine shaft 31. Or a connection key is formed on the power turbine shaft 31and a key groove is formed on the adapter shaft 20.
In some embodiments, the adaptor shaft 20 has an outwardly protruding protrusion, and the turbine rotor unit body 10 sleeved on the adaptor shaft 20 abuts against an end surface of the protrusion. This achieves axial positioning of the adapter shaft 20 and the turbine rotor unit 10. The aviation scroll engine includes a second fastener for fastening the turbine rotor unit body 10 with the adapter shaft 20. It will be appreciated that the second fastener may be a nut that is engaged with a threaded structure on the adapter shaft 20 to effect a secure connection.
In some embodiments, the aviation scroll engine comprises a rear support 71 and a rear bearing 72, the rear bearing 72 is provided on the rear support 71, and the adapter shaft 20 is inserted through the rear bearing 72 to be rotatably connected with the rear support 71. The radial position of the adapter shaft 20 is limited by the rear bearing 72, so that the coaxiality of the adapter shaft 20 and the rear bearing 72 is ensured, and the installation accuracy is improved. It will be appreciated that during replacement, when the adapter shaft 20 does not need to be disassembled, there is no risk of contamination of the rear bearing 72.
For the fixing manner of the rear bearing, in some embodiments, the rear supporting seat 71 has a bearing mounting hole, the rear bearing 72 is disposed in the bearing mounting hole, one end of the bearing mounting hole has an inwardly protruding baffle ring, and the outer ring of the rear bearing 72 abuts against the baffle ring. A third fastener is disposed at one end of the adapter shaft 20, and the third fastener is screwed to the adapter shaft 20 and abuts against the inner ring of the rear bearing 72. Therefore, the adapter shaft is convenient to assemble and disassemble.
In some embodiments, the adapter shaft 20 has a first adapter outer ring surface and a second adapter outer ring surface sequentially arranged along the second direction and sequentially increasing in diameter. Wherein the rear bearing 72 is located on the first transfer outer annulus, and the inner diameter of the rear bearing 72 matches the diameter of the first transfer outer annulus. The first mounting channel 10a of the turbine rotor unit body 10 is matched with the second transfer outer ring surface.
In some embodiments, the mounting end surface of the front support seat 33 has an axial dimension L2 with the end surface of the primary rotor 35 near the primary guide 80, the end surface of the primary rotor 35 near the primary guide 80 has an axial dimension L3 with the end surface of the second adjusting ring 322 facing away from the first adjusting ring 321, and the two axial end surfaces of the second adjusting ring 322 have an axial dimension T1 with a gap Z1 between the primary guide 80 and the primary rotor 35. Wherein L1, T1, L2, Z1, L3 constitute an assembly size chain.
The invention also provides an assembly method of the turbine shaft unit body 30, which is suitable for aviation turboshaft engines and comprises the following steps:
S1 determines a length dimension L1 between a mounting end surface of the front support seat 33 and a second end surface of the first adjustment ring 321 of the aviation scroll engine to be repaired.
The length dimension L1 may be obtained by: the length dimension between the mounting end face of the front support seat 33 of the detached turbine shaft unit body 30 and the second end face of the first adjustment ring 321 is acquired as the length dimension L1.
S2, selecting the next first adjusting ring 321, so that the dimension between the mounting end surface of the front support seat 33 to be mounted and the second end surface of the next first adjusting ring 321 meets the length dimension L1.
That is, the axial dimension between the power turbine shaft 31 to be mounted and the corresponding first adjustment ring 321 is matched with the disassembly, so that the direct assembly is possible. Here, satisfying the length dimension L1 means: the dimension between the mounting end surface of the front support seat 33 to be mounted and the second end surface of the next first adjusting ring 321 is close to the length dimension L1, and the difference therebetween meets the assembly tolerance requirement.
S3, the determined first adjusting ring 321 and the original second adjusting ring 322 are sleeved on the power turbine shaft 31 of the turbine shaft unit body 30 to be installed along the first direction, so that an assembly body is formed.
S4, the assembly is assembled to the adapter shaft 20 along the second direction and fastened and connected.
It will be appreciated that the above-described assembly method is applicable to replacement of a power turbine shaft 31, and that after removal of the turbine shaft unit 30 from the aero-turboshaft engine, which is to be replaced, a new turbine shaft unit 30 is replaced, wherein the first adjustment ring 321 needs to be redetermined based on the replacement power turbine shaft 31, and the second adjustment ring 322 does not need to be replaced. Of course, if damage occurs, a new second adjustment ring 322 of the same gauge may be selected.
It should be added that, before the turbine shaft unit 30 is assembled, high-speed dynamic balance of the power turbine shaft 31 needs to be completed, and the balance accuracy needs to meet the requirements of the aviation turboshaft engine, so as to ensure that the rotor dynamics of the power turbine shaft 31 is unchanged after interchange.
The invention also provides an assembling method of the turbine shaft unit body 30, which is suitable for an aviation turboshaft engine, wherein the aviation turboshaft engine comprises a primary guide 80, and one side of the primary rotor 35, which axially faces away from the secondary guide 36, is provided.
The assembly method comprises the following steps:
s1, determining a next second adjusting ring 322 according to a clearance Z1 between a first-stage guide 80 and a first-stage rotor 35 of the aviation scroll engine to be maintained.
It will be appreciated that as the size of the gap Z1 increases, the axial width of the second adjustment ring 322 also increases, both of which change in the same direction.
S2, the determined first adjusting ring 321 and the second adjusting ring 322 are sequentially sleeved on the power turbine shaft 31 of the turbine shaft unit body 30 to be installed along the first direction, so that an assembly body is formed.
S3, assembling the assembly body to the adapter shaft 20 along the second direction and fastening the assembly body.
It will be appreciated that the above-described assembly method is applicable to applications where the disassembled and repaired turbine shaft unit body 30 is assembled to other aviation scroll engines. Since the power turbine shaft 31 is matched with the first adjustment ring 321, replacement is not required. Only the second adjustment ring 322 need be redefined.
The invention also provides an assembling method of the turbine rotor unit body 10, which is suitable for aviation turboshaft engines and comprises the following steps:
S1, a gap Z2 between the primary rotor 35 and the secondary guide 36, and a gap Z3 between the secondary guide 36 and the second rotor are determined.
The gap Z2 between the primary rotor 35 and the secondary guide 36 can be determined from the detached turbine rotor unit 10 or from the turbine rotor unit 10 to be repaired.
S2, selecting the next second adjusting piece 38 according to the gap Z2 and the gap Z3, so that the gap between the primary rotor 35 and the secondary guide 36 of the turbine rotor unit body 10 to be mounted satisfies the dimension Z2, and the gap between the secondary guide 36 and the second rotor satisfies the dimension Z3.
S3, determining the axial size of the next second adjusting ring 322 according to the clearance Z1 between the primary guide 80 and the primary rotor 35 of the aviation scroll engine to be maintained.
And S4, grinding the next second adjusting ring 322 or replacing the second adjusting ring 322 with the corresponding axial size according to the determined axial size of the next second adjusting ring 322.
It will be appreciated that when the next second adjustment ring 322 is replaced, the first fastener 60 needs to be released, the adapter shaft 20 is removed together with the second adjustment ring 322, and then the replaced second adjustment ring 322 and the adapter shaft 20 are assembled and fastened in sequence. In other examples, the second adjustment ring 322 may be ground directly without removing the adapter shaft 20.
And S5, arranging the determined second adjusting piece 38 on the rear case 50.
S6, assembling the turbine shaft unit body 30 to be mounted to the adapter shaft 20 along the first direction and fastening and connecting.
It will be appreciated that the above-described assembly method is applicable to the assembly of the turbine rotor unit body 10.
Before the turbine rotor unit 10 is assembled, the primary rotor 35 and the secondary rotor 37 are required to be balanced in a combined mode, and the balance accuracy is required to meet the requirements of the aviation turboshaft engine, so that the characteristics of the rotors after interchange are consistent. Before the turbine rotor unit 10 is assembled, it is necessary to ensure that the air flow rate of the secondary guide 36 satisfies the requirements of the aviation turboshaft engine and that the aerodynamic performance after interchange is uniform.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. An aero-scroll engine that is easy to maintain, the aero-scroll engine comprising:
A turbine rotor unit body (10), the turbine rotor unit body (10) having a first mounting channel (10 a) extending axially;
the turbine rotor unit body (10) can be sleeved on the transfer shaft (20) along a first direction or can be moved out of the transfer shaft (20) along a second direction opposite to the first direction, the transfer shaft (20) is fixedly connected with the turbine rotor unit body (10) so as to limit the relative movement of the two, and the transfer shaft (20) is provided with a second installation channel (20 a) coaxial with the first installation channel (10 a);
The turbine shaft unit body (30) comprises a power turbine shaft (31), one end of the power turbine shaft (31) is coaxially arranged in the second installation channel (20 a), the power turbine shaft (31) can be inserted into the switching shaft (20) along the second direction or removed out of the switching shaft (20) along the first direction, the switching shaft (20) and the power turbine shaft (31) are fixedly connected to limit relative movement of the switching shaft (20) and the power turbine shaft (31), and rotation of the turbine rotor unit body (10) can be transmitted to the turbine shaft unit body (30) through the switching shaft (20);
The power turbine shaft (31) is axially arranged, a first step surface (31 a) is formed on the power turbine shaft (31), and a second step surface (20 b) axially opposite to the first step surface (31 a) is formed on the adapter shaft (20); the turbine shaft unit body (30) comprises a first adjusting piece (32), the first adjusting piece (32) is sleeved on the turbine shaft unit body (30) along a first direction, a first end face of the first adjusting piece (32) is abutted to a first step face (31 a) of the power turbine shaft (31), and a second end face of the first adjusting piece (32) is abutted to a second step face (20 b) of the switching shaft (20);
The aviation turboshaft engine comprises a front casing (40) positioned at one end of the power turbine shaft (31) far away from the turbine rotor unit body (10); the turbine shaft unit body (30) comprises a front supporting seat (33) and a front bearing (34), the front supporting seat (33) is fixedly connected with a front casing (40), the front bearing (34) is arranged on the front supporting seat (33), and one end of the power turbine shaft (31) is arranged in the front bearing (34) in a penetrating mode so as to be connected with the front supporting seat (33) in a rotating mode.
2. The maintenance-friendly aviation scroll engine of claim 1 wherein,
The first adjusting piece (32) comprises a first adjusting ring (321) and a second adjusting ring (322) which are sequentially arranged along the second direction and mutually abutted.
3. The maintenance-friendly aviation scroll engine of claim 2 wherein,
The front supporting seat (33) is provided with a mounting end face matched with the front casing (40), the first adjusting ring (321) is provided with a ring end face abutting against the second adjusting ring (322), and the first adjusting ring (321) is used for enabling the axial dimension between the mounting end face and the ring end face to be a preset value.
4. The maintenance-friendly aviation scroll engine of claim 2 wherein,
The turbine rotor unit body (10) comprises a primary rotor (35), a secondary guide (36) and a secondary rotor (37) which are sequentially arranged along the axial direction, the aviation turboshaft engine comprises a primary guide (80) arranged on one side, deviating from the secondary guide (36) in the axial direction, of the primary rotor (35), and the second adjusting ring is used for adjusting a gap between the primary guide (80) and the primary rotor (35).
5. The maintenance-friendly aviation scroll engine of claim 1 wherein,
The outer peripheral wall of the power turbine shaft (31) is provided with at least two mounting shaft faces which are sequentially arranged along a second direction and the diameters of which are sequentially reduced, the inner annular wall of the transfer shaft (20) is provided with at least two transfer inner annular faces which are sequentially arranged along the second direction and the diameters of which are sequentially increased, and each mounting shaft face is matched with the corresponding transfer inner annular face.
6. The maintenance-friendly aviation scroll engine as claimed in any one of claims 1-2, wherein,
The turbine rotor unit body (10) comprises a primary rotor (35), a secondary guide (36) and a secondary rotor (37) which are sequentially arranged along the axial direction, and the aviation turboshaft engine further comprises a rear casing (50) positioned at one side of the secondary guide (36) radially outwards;
the turbine rotor unit body (10) comprises a second adjusting piece (38), wherein the second adjusting piece (38) is axially positioned between the rear casing (50) and the secondary guide (36) so as to adjust the axial position of the secondary guide (36) between the primary rotor (35) and the secondary rotor (37).
7. The maintenance-friendly aviation scroll engine as claimed in any one of claims 1-2, wherein said aviation scroll engine comprises a rear support base (71) and a rear bearing (72), said rear bearing (72) is provided to said rear support base (71), and said adapter shaft (20) is provided through said rear bearing (72) to be rotatably connected to said rear support base (71).
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| CN202410722300.4A CN118346391B (en) | 2024-06-05 | 2024-06-05 | Aviation turboshaft engine easy to maintain |
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| CN202410722300.4A CN118346391B (en) | 2024-06-05 | 2024-06-05 | Aviation turboshaft engine easy to maintain |
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| CN118346391B (en) | 2024-10-01 |
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