CN109322848B - Rotor assembly of gas compressor test piece and gas compressor test piece - Google Patents
Rotor assembly of gas compressor test piece and gas compressor test piece Download PDFInfo
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- CN109322848B CN109322848B CN201810998817.0A CN201810998817A CN109322848B CN 109322848 B CN109322848 B CN 109322848B CN 201810998817 A CN201810998817 A CN 201810998817A CN 109322848 B CN109322848 B CN 109322848B
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- 238000012360 testing method Methods 0.000 title claims abstract description 81
- 238000007789 sealing Methods 0.000 claims description 11
- 230000005540 biological transmission Effects 0.000 claims description 6
- 230000000149 penetrating effect Effects 0.000 claims 1
- 238000002360 preparation method Methods 0.000 claims 1
- 238000005452 bending Methods 0.000 abstract description 9
- 238000013461 design Methods 0.000 abstract description 8
- 238000004458 analytical method Methods 0.000 description 5
- 230000009467 reduction Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000005461 lubrication Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
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- 238000002485 combustion reaction Methods 0.000 description 1
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- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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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
- F04D25/00—Pumping installations or systems
- F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
- F04D25/163—Combinations of two or more pumps ; Producing two or more separate gas flows driven by a common gearing arrangement
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
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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
- F04D29/601—Mounting; Assembling; Disassembling specially adapted for elastic fluid pumps
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/662—Balancing of rotors
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a rotor assembly of a gas compressor test piece and the gas compressor test piece, wherein the rotor assembly comprises: the gas compressor blade disc is used for increasing gas flow velocity and gas pressure, the balance disc is used for balancing axial acting force and is coaxial with the gas compressor blade disc, the center pull rod is used for tensioning the rotor assembly and transmitting the axial force, the center pull rod penetrates through and locks the gas compressor blade disc and the balance disc, the power input shaft is used for torque transmitting the axial force and is fixedly connected with the balance disc, and the support structure is used for supporting the rotor assembly on the casing and comprises a first support piece and a second support piece, the first support piece and the second support piece are respectively arranged at the front end and the rear end of the gas compressor blade disc, and the balance disc is arranged behind the second support piece. The structural design of the invention obviously reduces the supporting span of the rotor, reduces the bending deflection generated when the rotor component rotates, enhances the rigidity strength of the rotor component, and improves the critical rotating speed margin of the rotor component.
Description
Technical Field
The invention relates to the field of aeroengine test pieces, in particular to a rotor assembly of a compressor test piece. In addition, the invention also relates to a compressor test piece comprising the rotor assembly of the compressor test piece.
Background
The aircraft engine is a highly complex and precise thermal machine, provides the aircraft with the power required by flight, and the performance of the aircraft engine is continuously improved along with the development of science and technology. After the overall structure of the engine is determined, test pieces are designed for all parts of the engine, such as a gas compressor, a combustion chamber, a turbine and the like, and are tested to obtain the aerodynamic performance and the vibration characteristics of the parts, so that support is provided for matching and optimizing and improving the parts of the whole engine.
Compared with an engine, the axial force of the compressor test piece cannot realize self balance, a balance structure must be added on a rotor, otherwise the axial force damages a bearing. When a gas compressor test piece is subjected to a performance test, the problems that the rotor and the stator are rubbed and abraded due to overlarge deformation of the rotor, further serious vibration is caused, and the blade is damaged or the test piece is damaged exist.
Disclosure of Invention
The invention provides a rotor assembly of a gas compressor test piece and the gas compressor test piece, and aims to solve the technical problems that the rotor is weak in rigidity and insufficient in critical rotation speed due to bending deflection easily generated by a rotor when the rotor assembly of the gas compressor test piece rotates.
The technical scheme adopted by the invention is as follows:
a rotor assembly for a compressor test piece, the rotor assembly comprising: the gas compressor blade disc is used for increasing gas flow velocity and gas pressure, the balance disc is used for balancing axial acting force and is coaxial with the gas compressor blade disc, the center pull rod is used for tensioning the rotor assembly and transmitting the axial force, the center pull rod penetrates through and locks the gas compressor blade disc and the balance disc, the power input shaft is used for torque transmitting the axial force and is fixedly connected with the balance disc, and the support structure is used for supporting the rotor assembly on the casing and comprises a first support piece and a second support piece, the first support piece and the second support piece are respectively arranged at the front end and the rear end of the gas compressor blade disc, and the balance disc is arranged behind the second support piece.
Further, the compressor blade disc comprises an axial flow first-stage blade disc, an axial flow second-stage blade disc and a centrifugal impeller which are sequentially arranged; the axial flow second-stage blade disc is provided with a first shaft neck extending out of the inner cavity of the compressor blade disc for radial limiting, and the first shaft neck is provided with a first supporting piece positioned at the disc center of the axial flow first-stage blade disc; the second support member is mounted on the second journal at the rear end of the centrifugal impeller.
Further, the first supporting piece comprises a first free end used for being rotatably connected to the first journal and a second free end used for being rotatably connected and fixedly connected with the casing; the first free end is connected with the second free end through a ball bearing; the second supporting piece comprises a third free end, a fourth free end and a third free end, wherein the third free end is used for being rotatably connected to the second journal, and the fourth free end is used for being rotatably connected and fixedly connected with the casing; the third free end and the fourth free end are connected through a roller bearing.
Furthermore, the axial flow first-stage blade disc, the axial flow second-stage blade disc and the first journal are of an integrated structure.
Furthermore, the axial flow first-stage blade disc is arranged in a cantilever mode.
Furthermore, the axial flow second-stage blade disc and the centrifugal impeller adopt end teeth for centering and torque transmission; the centrifugal impeller and the balance disc are positioned and connected by a spigot; the centrifugal impeller and the balance disc adopt spline torque transmission.
Furthermore, the balance disc and the power input shaft adopt at least one of spigot positioning connection, nested connection or multipoint bolt connection; or the balance disc and the power input shaft adopt at least one of multipoint connection, line connection or surface connection; the connection part of the balance disc and the power input shaft is provided with a sealing labyrinth.
Furthermore, the first end of the central pull rod is connected with the balance disc through a bolt, and the second end of the central pull rod penetrates through and locks the first journal; the center link and the first journal are at least one of bolt lock, latch lock, chute lock, slide lock, or wedge lock.
Furthermore, a sealing labyrinth is arranged at least one of the positions between the first supporting piece and the casing, between the second supporting piece and the casing, between the rear end cavity of the compressor blade disc and the casing or between the compressor blade disc and the balance disc; the radial direction of the balance disc is provided with a sealing labyrinth which is in clearance fit with the casing; the first-stage blade disc is provided with a balance piece which is used for adjusting the dynamic balance of the rotor assembly and is detachable on the first-stage blade disc; the balancing piece adopts at least one of a balancing block, a balancing strip or a balancing surface.
According to another aspect of the invention, a compressor test piece is further provided, and the compressor test piece comprises a rotor assembly of the compressor test piece.
The invention has the following beneficial effects:
the rotor assembly of the compressor test piece comprises a compressor blade disc, a balance disc, a power input shaft, a center pull rod and a support structure, the rotor assembly of the compressor test piece is of a double-support structure, no support is arranged behind the balance disc, the support structure is arranged at the front end and the rear end of the compressor blade disc according to the support layout of a 1-1-0 mode, and the balance disc is arranged behind the second support piece. The structural design of the rotor assembly of the compressor test piece reduces the supporting span between the first supporting piece and the second supporting piece, the supporting is not arranged behind the balance disc, and only two supporting pieces are adopted, so that the distance of the rotor assembly span is effectively shortened. On one hand, the span of the supporting structure and the rigidity of the rotor assembly are in an inverse proportional relation, the rigidity of the rotor assembly is obviously increased along with the reduction of the span of the supporting structure, the bending deflection generated when the rotor assembly rotates is reduced, and the operation reliability is improved; on the other hand, the span of the rotor assembly is in inverse proportion relation with the critical rotating speed, so that the working rotating speed of the rotor assembly is far away from the critical rotating speed margin by adjusting the span of the rotor assembly, and the vibration risk is effectively reduced.
The structural design of the rotor assembly of the gas compressor test piece obviously reduces the supporting span of the rotor, is beneficial to reducing the bending deflection generated when the rotor assembly rotates, enhances the rigidity strength of the rotor assembly, improves the critical rotating speed margin of the rotor assembly and improves the operation reliability of the rotor assembly. The rotor assembly of the compressor test piece is arranged into a double-support structure, a first support piece and a second support piece, the reduction of the support pieces can save the lubrication of the support pieces and seal the air-entraining structure, and the processing and test cost is reduced. Through test tests, the rotor assembly of the compressor test piece is safe and stable in operation, and the problems of local bending vibration caused by unbalance, resonance caused by insufficient critical rotating speed margin and the like do not occur.
The gas compressor test piece adopts the rotor component of the gas compressor test piece, remarkably reduces the supporting span of the rotor, and ensures that the gas flow at the outlet of the gas compressor flows out along the radial direction. The gas compressor test piece has a simple structure, runs stably, obtains stable test data, and meets the test requirements of the engine.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic view of a rotor assembly of a compressor test piece of the present embodiment of the present invention.
Description of reference numerals:
1. a compressor blade disk; 11. an axial flow first stage bladed disk; 12. an axial flow second stage bladed disk; 13. a centrifugal impeller; 2. a balance disc; 3. a power input shaft; 4. a central pull rod; 5. a support structure; 51. a first support member; 52. a second support member; 121. a first journal; 131. and a second journal.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a schematic view of a rotor assembly of a compressor test piece of the present embodiment of the present invention.
As shown in fig. 1, the rotor assembly of the compressor test piece of the present embodiment includes: the compressor blade disc 1 is used for increasing the gas flow rate and the gas pressure, the balance disc 2 is used for balancing the axial acting force and is coaxially arranged with the compressor blade disc 1, the central pull rod 4 is used for tensioning a rotor assembly and transmitting the axial force, the central pull rod 4 penetrates through and locks the compressor blade disc 1 and the balance disc 2, the power input shaft 3 is used for transmitting the axial force through torque and is fixedly connected with the balance disc 2, the support structure 5 is used for supporting the rotor assembly on a casing, the support structure 5 comprises a first support piece 51 and a second support piece 52, the first support piece 51 and the second support piece 52 are respectively arranged at the front end and the rear end of the compressor blade disc 1, and the balance disc 2 is arranged behind the second support piece 52. The rotor assembly of the compressor test piece comprises a compressor blade disc 1, a balance disc 2, a power input shaft 3, a central pull rod 4 and a support structure 5, the rotor assembly of the compressor test piece is arranged into the double support structure 5, no support is arranged behind the balance disc, the support structures 5 are arranged at the front end and the rear end of the compressor blade disc 1 according to the support layout in a 1-1-0 mode, and the balance disc 2 is arranged behind a second support piece 52. The structural design of the rotor assembly of the compressor test piece reduces the supporting span between the first supporting piece 51 and the second supporting piece 52, no support is arranged behind the balance disc 2, and only two supporting pieces are adopted, so that the distance of the rotor assembly span is effectively shortened. On one hand, the span of the supporting structure 5 and the rigidity of the rotor assembly are in an inverse proportional relation, the rigidity of the rotor assembly is obviously increased along with the reduction of the span of the supporting structure 5, the bending deflection generated when the rotor assembly rotates is reduced, and the operation reliability is improved; on the other hand, the span of the rotor assembly is in inverse proportion relation with the critical rotating speed, so that the working rotating speed of the rotor assembly is far away from the critical rotating speed margin by adjusting the span of the rotor assembly, and the vibration risk is effectively reduced.
The rotor assembly of the compressor test piece is arranged to be a double-support structure 5, the balance disc 2 is arranged behind the second support piece 52, the rotor span between the double-support structure 5 is effectively reduced, and the rotor span influences the rigidity of the rotor and a key factor of the critical rotating speed.
The formula (I) is a rigidity estimation formula of a simply-supported rotor at two ends, wherein delta is approximately constant (the same below),lis the relationship between the span, stiffness and deformation of the supporting structureKx=FIt can be seen that as the span of the support structure increases, the rotor rotating at high speed deforms more and more under the action of residual unbalance, and excessive deformation inevitably leads to excessive scraping and rubbing of the blades and the casing, thereby causing harmful vibration and even serious accidents.
The formula (two) is a critical rotation speed estimation formula,dis the outer diameter of the rotor and is,lis the rotor span. Under normal circumstancesdThe value is limited by the size of the engine, and cannot be changed after being determined,lis the most critical factor affecting the rotor. In the formulalThe reduction is 50%, the critical rotating speed is increased by 4 times, so that the rotation speed can be adjustedlCritical rotation of rotorThe working speed is kept away, the critical speed margin of the rotor is improved, and the vibration risk is reduced.
In conclusion, the rotor span is an important parameter influencing the vibration and deformation of the rotor, and the vibration characteristic of the rotor can be optimized by shortening the span, so that the risk of test failure and possible economic loss are reduced. According to the arrangement of the rotor assembly of the compressor test piece, the supporting structures 5 are arranged at the front end and the rear end of the compressor blade disc 1, and the balance disc 2 is arranged behind the second supporting piece 52, so that the span of the supporting structures 5 is effectively reduced, and the vibration characteristic of the rotor is improved.
The structural design of the rotor assembly of the gas compressor test piece obviously reduces the supporting span of the rotor, is beneficial to reducing the bending deflection generated when the rotor assembly rotates, enhances the rigidity strength of the rotor assembly, improves the critical rotating speed margin of the rotor assembly, and improves the operation reliability of the rotor assembly. The rotor assembly of the compressor test piece is arranged into a double-support structure: the first supporting piece 51 and the second supporting piece 52 can save the lubrication of the supporting pieces and seal the air-guiding structure, and reduce the processing and testing cost. Through test tests, the rotor assembly of the compressor test piece is safe and stable in operation, and the problems of local bending vibration caused by unbalance, resonance caused by insufficient critical rotating speed margin and the like do not occur.
As shown in fig. 1, in the present embodiment, the compressor bladed disk 1 includes an axial flow first stage bladed disk 11, an axial flow second stage bladed disk 12 and a centrifugal impeller 13, which are sequentially arranged. The compressor blade disc 1 comprises a secondary axial flow stage blade disc and a primary centrifugal impeller 13, and the invention is not only suitable for a secondary axial flow stage blade, but also suitable for a three-stage axial flow stage blade, a four-stage axial flow stage blade disc and the like. Optionally, the axial flow second-stage bladed disk 12 is provided with a first journal 121 extending along the inner cavity of the compressor bladed disk 1 for radial position limitation, and the first journal 121 is provided with a first support member 51 at the disk center position of the axial flow first-stage bladed disk 11. The axial flow second stage bladed disk 12 is provided with a first journal 121, and the first supporting member 51 is located at the disk center position of the axial flow first stage bladed disk 11. The internal space of the rotor assembly of the compressor test piece is reasonably utilized, the span distance of the rotor assembly is saved, the first supporting piece 51 is positioned at the center of the axial flow first-stage blade disc 11, and the optimal structural design is optimized through the analysis of limiting elements and the analysis of strength, deformation and vibration tests. Optionally, the second support 52 is mounted on a second journal 131 at the rear end of the centrifugal impeller 13. The second supporting piece 52 is arranged on the second journal 131, the balance disc 2 is connected with the centrifugal impeller 13, an end tooth connecting structure in the prior art is omitted, and the processing cost is reduced. The balance disc 2 and the centrifugal blades are matched through the connecting spigot to conduct rotor stability test research. The balance disc 2 is arranged at the rear end of the centrifugal impeller 13 for rotor deformation, theoretical analysis and experimental research. The rotor assembly of the compressor test piece with the balance disc 2 arranged behind the centrifugal impeller 13 is stable in structure, does not cause local bending vibration, and is safe and stable in operation.
As shown in fig. 1, in the present embodiment, the first supporting member 51 includes a first free end for rotatably connecting to the first journal 121, and a second free end for rotatably connecting to the casing; the first free end is connected with the second free end through a ball bearing. A second support 52 comprising a third free end for rotating connection to the second journal 131, a fourth free end for rotating connection to the casing; the third free end and the fourth free end are connected through a roller bearing. The rotor assembly of the gas compressor test piece adopts a 2-pivot structure, the roller bearing and the ball bearing bear the weight of the whole gas compressor test piece and the axial force of the rotor assembly of the gas compressor test piece, and the axial force is transmitted to the casing through the ball bearing and the roller bearing and is finally transmitted to the test bed.
As shown in fig. 1, in the present embodiment, the axial flow first stage bladed disk 11, the axial flow second stage bladed disk 12 and the first journal 121 are of an integral structure. The integral structure integrally manufactured and formed is adopted to increase the rigidity strength of the rotor assembly of the compressor test piece, and the integral structure is simple in structure and low in manufacturing cost.
As shown in FIG. 1, in this embodiment, the axial flow first stage blade disk 111 is cantilevered. The integral structural design of the axial flow first-stage bladed disc 11, the axial flow second-stage bladed disc 12 and the first journal 121 comprises finite element analysis, strength, deformation and vibration test analysis, and can be used only when the design target is met, otherwise, the integral structure can be optimally designed. The axial flow first stage blade disc 11 and the axial flow second stage blade disc 12 can be connected by welding. In order to meet the requirement that the first shaft neck 121 is located at the center of the axial flow first-stage blade disc 11, the first-stage blade disc 11 and the second-stage blade disc 12 with the first shaft neck 121 are welded after rough machining is finished, and the welding quality directly determines whether a semi-finished product can be used continuously, so that the requirement on a welding process is high.
In the present embodiment, as shown in fig. 1, the axial flow second stage bladed disk 12 and the centrifugal impeller 13 adopt end tooth centering torque transmission. The centrifugal impeller 13 is connected with the balance disc 2 in a spigot positioning way. The centrifugal impeller 13 and the balance disk 2 adopt spline transmission. And the structural stability of a rotor assembly of the compressor test piece is enhanced.
In the present embodiment, as shown in fig. 1, the balance disc 2 and the power input shaft 3 are at least one of a spigot-positioning connection, a nested connection, or a multi-point bolt connection. Alternatively, the balance disc 2 and the power input shaft 3 adopt at least one of multipoint connection, line connection or surface connection. Alternatively, the balance disc 2 and the power input shaft 3 are connected through bolts which are evenly distributed in the circumferential direction. The bolted connection of above-mentioned circumference equipartition has the effect to reduce power input shaft section length, simplifies balance disc 2 and 3 connection structure of power input shaft, effectively reduces the length of power input section, shortens rotor span length, reduces the too big risk of amplitude between balance disc 2 and the power input shaft 3. Optionally, a sealing labyrinth is arranged at the joint of the balance disc 2 and the power input shaft 3, so that good sealing is favorably formed.
As shown in fig. 1, in the present embodiment, a first end of the central rod 4 is connected to the balance disc 2 by a screw, and a second end of the central rod 4 penetrates and locks the first journal 121. The center link 4 and the first journal 121 are at least one of bolt lock, latch lock, slide lock, or wedge lock. The central pull rod 4 tensions a rotor assembly of the compressor test piece and ensures the reliability and the integral rigidity of connection of all levels. The first journal 121 is arranged at the center of the first supporting part 51 of the axial flow first-stage blade disc 11, the length of the central pull rod 4 is effectively reduced, the overall structure of the rotor assembly is more compact, the deformation of the rotor assembly is reduced, and the vibration risk is reduced.
As shown in fig. 1, in the present embodiment, a sealing labyrinth is disposed at least one of the positions between the first support member 51 and the casing, between the second support member 52 and the casing, between the rear end cavity of the compressor blade disc 1 and the casing, or between the compressor blade disc 1 and the balance disc 2. The second free end of the first supporting member 51 and the fourth free end of the second supporting member 52 are assembled on the bearing seat of the casing, and are in clearance fit with the sealing coating on the bearing seat, so that the clearance of each part is reduced, air leakage is prevented, and the stability of the whole device is ensured.
In this embodiment, the balance disc 2 is provided with a sealing labyrinth in the radial direction to be in clearance fit with the casing. The grate of the balance disc 2 forms a seal with the inner cavity of the casing. Optionally, the number of the grate teeth of the balance disc 2 is at least 7, and the grate teeth of the balance disc 2 are flat teeth. The number of the grid teeth can be set according to the actual situation. In this embodiment, the first stage bladed disk 11 is provided with a balancing member for adjusting the dynamic balance of the rotor assembly and detachably attached to the bladed disk 11. The balancing piece adopts at least one of a balancing block, a balancing strip or a balancing surface. By increasing or adjusting the number and the positions of the balance pieces, the dynamic balance precision of the rotor assembly of the gas compressor test piece can be adjusted, and the stable operation of the rotor assembly of the gas compressor test piece is ensured.
According to another aspect of the invention, a compressor test piece is further provided, and the compressor test piece comprises a rotor assembly of the compressor test piece. The gas compressor test piece adopts the rotor component of the gas compressor test piece, remarkably reduces the supporting span of the rotor, and ensures that the gas flow at the outlet of the gas compressor flows out along the radial direction. The gas compressor test piece has a simple structure, runs stably, obtains stable test data, and meets the test requirements of the engine.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. 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 (9)
1. A rotor assembly of a compressor test piece, the rotor assembly comprising:
a compressor bladed disk (1) for increasing the gas flow rate and the gas pressure,
a balancing disk (2) which is used for balancing axial acting force and is coaxially arranged with the compressor blade disk (1),
a central tie rod (4) for tensioning the rotor assembly and transmitting axial forces, the central tie rod (4) penetrating and locking the compressor blade disc (1) and the balancing disc (2),
a power input shaft (3) used for transmitting axial force by torque and fixedly connected with the balance disc (2),
a support structure (5) for supporting the rotor assembly on a casing,
it is characterized in that the preparation method is characterized in that,
the support structure (5) comprises a first support (51) and a second support (52), the first support (51) and the second support (52) being respectively arranged at the front end and the rear end of the compressor blade disc (1), the balancing disc (2) being arranged behind the second support (52);
the compressor blade disc (1) comprises an axial flow first-stage blade disc (11), an axial flow second-stage blade disc (12) and a centrifugal impeller (13) which are sequentially arranged;
a first shaft neck (121) extending out along the inner cavity of the compressor blade disc (1) and used for radial limiting is arranged on the axial flow second-stage blade disc (12), and a first supporting piece (51) located at the disc center position of the axial flow first-stage blade disc (11) is installed on the first shaft neck (121);
the second support member (52) is mounted on a second journal (131) at the rear end of the centrifugal impeller (13).
2. The rotor assembly of a compressor test piece according to claim 1,
the first supporting piece (51) comprises a first free end used for being rotatably connected to the first shaft neck (121), and a second free end used for being rotatably connected and fixedly connected with a casing;
the first free end is connected with the second free end through a ball bearing;
the second supporting piece (52) comprises a third free end for being rotatably connected to the second journal (131), and a fourth free end for being rotatably connected to the casing and fixedly connected to the casing;
the third free end and the fourth free end are connected through a roller bearing.
3. The rotor assembly of a compressor test piece according to claim 1,
the axial flow first-stage blade disc (11), the axial flow second-stage blade disc (12) and the first shaft neck (121) adopt an integral structure.
4. The rotor assembly of a compressor test piece according to claim 1,
the axial flow first-stage blade disc (11) is distributed by adopting a cantilever.
5. A rotor assembly for a compressor test piece according to claim 4,
the axial flow second-stage blade disc (12) and the centrifugal impeller (13) adopt end tooth centering torque transmission;
the centrifugal impeller (13) is connected with the balance disc (2) in a spigot positioning way;
the centrifugal impeller (13) and the balance disc (2) adopt spline torque transmission.
6. The rotor assembly of a compressor test piece according to claim 1,
the balance disc (2) and the power input shaft (3) are in at least one of spigot positioning connection, nested connection or multipoint bolt connection; or
The balance disc (2) and the power input shaft (3) adopt at least one of multipoint connection, line connection or surface connection;
and a sealing labyrinth is arranged at the joint of the balance disc (2) and the power input shaft (3).
7. The rotor assembly of a compressor test piece according to claim 1,
the first end of the central pull rod (4) is connected with the balance disc (2) through a bolt, and the second end of the central pull rod (4) penetrates through and locks the first journal (121);
the central pull rod (4) and the first journal (121) adopt at least one of bolt locking, sliding groove locking, sliding block locking or wedge block locking.
8. The rotor assembly of a compressor test piece according to claim 1,
at least one of the positions between the first supporting piece (51) and the casing, between the second supporting piece (52) and the casing, between the rear end cavity of the compressor blade disc (1) and the casing or between the compressor blade disc (1) and the balance disc (2) is provided with a sealing labyrinth;
the balance disc (2) is provided with a sealing labyrinth in the radial direction to be in clearance fit with the casing;
the first-stage blade disc (11) is provided with a balance piece which is used for adjusting the dynamic balance of the rotor assembly and is detachable on the first-stage blade disc (11);
the balancing piece adopts at least one of a balancing block, a balancing strip or a balancing surface.
9. A compressor test piece comprising a rotor assembly of the compressor test piece of any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810998817.0A CN109322848B (en) | 2018-08-30 | 2018-08-30 | Rotor assembly of gas compressor test piece and gas compressor test piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810998817.0A CN109322848B (en) | 2018-08-30 | 2018-08-30 | Rotor assembly of gas compressor test piece and gas compressor test piece |
Publications (2)
| Publication Number | Publication Date |
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| CN109322848A CN109322848A (en) | 2019-02-12 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110132556B (en) * | 2019-04-30 | 2021-11-12 | 中国航发湖南动力机械研究所 | Modular turbine test piece and test method thereof |
| CN112012966B (en) * | 2019-05-29 | 2022-05-31 | 中国航发商用航空发动机有限责任公司 | Balancing assembly, rotor system, gas turbine and balancing method |
| CN111312058B (en) * | 2019-11-29 | 2022-02-25 | 中国科学院工程热物理研究所 | Test piece structure of gas compressor |
| CN111335966A (en) * | 2020-03-25 | 2020-06-26 | 中国航发哈尔滨东安发动机有限公司 | Variable blade tip size control mounting structure of high-speed engine compressor |
| CN112160794B (en) * | 2020-09-18 | 2023-02-17 | 中国航发四川燃气涡轮研究院 | Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine |
| CN112228382B (en) * | 2020-12-17 | 2021-03-02 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor performance test device |
| CN112983651B (en) * | 2021-04-26 | 2023-07-28 | 黄锴 | Small aviation double-rotor unmanned aerial vehicle engine |
| CN113357201B (en) * | 2021-07-22 | 2023-02-28 | 中国航发沈阳发动机研究所 | Balance structure and balancing method for low-pressure rotor local machine of aircraft engine |
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| US4177692A (en) * | 1977-11-25 | 1979-12-11 | General Motors Corporation | Shaft balancing |
| JPH02196137A (en) * | 1989-01-25 | 1990-08-02 | Ishikawajima Harima Heavy Ind Co Ltd | Gas turbine |
| DE102010009566A1 (en) * | 2010-02-26 | 2011-09-01 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Radial or diagonal fan wheel |
| CN105971920B (en) * | 2016-06-22 | 2018-01-30 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Compressor test device |
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