CN114166393A - Blade dynamic stress measuring structure - Google Patents
Blade dynamic stress measuring structure Download PDFInfo
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- CN114166393A CN114166393A CN202111325802.6A CN202111325802A CN114166393A CN 114166393 A CN114166393 A CN 114166393A CN 202111325802 A CN202111325802 A CN 202111325802A CN 114166393 A CN114166393 A CN 114166393A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0004—Force transducers adapted for mounting in a bore of the force receiving structure
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
The invention discloses a blade dynamic stress measuring structure, which comprises: the device comprises a turbine shaft, a stress measuring device, a switching shaft set and a mounting seat assembly, wherein two ends of the switching shaft set are respectively connected with the turbine shaft and the stress measuring device, and the turbine shaft, the switching shaft set and the stress measuring device are respectively arranged in the mounting seat assembly. The stress measuring device is also sleeved with a gas-guiding cooling pipe group, the first end of the gas-guiding cooling pipe group is closed and communicated with an external cold air supply source, and the opposite second end of the gas-guiding cooling pipe group is hermetically connected with the mounting seat assembly to form a closed cover. The measuring and feeding line set extends along the bleed air cooling pipe set and then extends outwards from the first end of the bleed air cooling pipe set. The invention designs a blade dynamic stress measuring structure which can measure the dynamic stress of a blade at the rear end of an engine turbine, thereby effectively avoiding the situation that a stress measuring device is inconvenient to arrange when a speed reducer or an accessory transmission device exists at the front end of the engine, and meeting the situation that the stress measuring device is not suitable for being arranged in the front for measuring the dynamic stress.
Description
Technical Field
The invention relates to the technical field of blade dynamic stress measurement, in particular to a blade dynamic stress measurement structure.
Background
For an aircraft engine or a gas turbine, a blade is one of the most important parts which are easy to break down, and the structure and the working environment of the blade are quite complex no matter a compressor blade or a turbine blade, so that in the development process, the dynamic stress of the blade needs to be measured to obtain the steady state stress, the resonant frequency and the resonant stress of the blade in the full-speed state, and the durability and the stress level of the blade in all working states are evaluated.
The equipment for measuring dynamic stress is called as an electrical igniter, belongs to a precision instrument, has strict limitation on the temperature of the working environment, is limited by the size of the electrical igniter, and has limited available space for an engine. At present, for measuring dynamic stress of a gas compressor and a turbine blade, a part of an engine body is remanufactured at the front end of the engine so as to be matched with the installation of a current leading device.
Fig. 1 shows a dynamic stress measuring device of the prior art, which adopts a mode of leading an electrical appliance in front and aims at the condition that a speed reducer and an accessory transmission device are not arranged at the front end of an engine. The method is characterized in that the front end part of an engine is subjected to complementary processing to be matched with the installation of an electrical igniter, a connecting shaft is designed to be used for connecting the electrical igniter and an output shaft switching section of the engine, a dynamic stress strain gage is pasted on a gas compressor or a turbine blade, then a test wire connected with the strain gage is led out from a processing hole on an output shaft of a power turbine, finally the interior of the electrical igniter is connected, a static-static conversion brush wire structure exists in the electrical igniter, a test signal of the dynamic stress test wire rotating along with the blade is connected with external receiving equipment through a static output wire through the brush wire structure, the interior of the electrical igniter is cooled through a cooling liquid pipe, and the interior of the electrical igniter is lubricated through an oil pipe.
Aiming at the condition that the front end of an engine is not provided with a speed reducer and an accessory transmission device, if the speed reducer or the accessory transmission device is positioned at the front end of the engine, the speed reducer part or the accessory transmission device needs to be subjected to complementary processing, the structures of the speed reducer and the accessory transmission device are quite complex, a large number of gear structures are involved inside the speed reducer and the accessory transmission device, and the speed reducer or the accessory transmission device is basically not subjected to remaking processing conditions unless the speed reducer or the accessory transmission device specially used for dynamic stress measurement is designed, so that on one hand, the period of redesigning is long, and the time and the economic cost are high; on the other hand, whether the redesigned accessory drive meets engine operating requirements requires re-evaluation. Therefore, no matter the speed reducer or the accessory transmission is positioned at the front end of the engine, the leading device is not well operated, even the situation that the leading device cannot be realized occurs, and the application range of the existing scheme has great limitation.
Disclosure of Invention
The invention provides a blade dynamic stress measuring structure, which aims to solve the technical problem that a stress measuring device is inconvenient to arrange when a speed reducer or an accessory transmission device exists at the front end of an engine.
The technical scheme adopted by the invention is as follows:
a blade dynamic stress measuring structure comprising: the device comprises a turbine shaft, a stress measuring device, a switching shaft group and a mounting seat assembly, wherein the turbine shaft is used for mounting a turbine disc with working blades, the stress measuring device is used for measuring the dynamic stress of the blades, the switching shaft group plays a switching role, the mounting seat assembly plays a mounting and supporting role, the output end of the turbine shaft is arranged at an interval with the stress measuring device, two ends of the switching shaft group are respectively connected with the turbine shaft and the stress measuring device, and the turbine shaft, the switching shaft group and the stress measuring device are respectively arranged in the mounting seat assembly; the stress measuring device is also sleeved with a gas-guiding cooling pipe set used for introducing external cold air, the first end of the gas-guiding cooling pipe set is closed and is communicated with a cold air supply source supplying the external cold air, and the opposite second end of the gas-guiding cooling pipe set is hermetically connected with the mounting seat assembly to form a closed cover, so that the introduced cold air cools the turbine shaft, the adapter shaft set and the stress measuring device; the measuring and supplying line set is used for respectively measuring the dynamic stress of the working blade and the internal and external temperature and pressure of a bearing cavity formed in the mounting seat assembly, supplying cooling liquid and lubricating oil to the stress measuring device, and extends outwards from the first end of the bleed air cooling pipe set after extending along the bleed air cooling pipe set.
Furthermore, the stress measuring device comprises an electrical lead coaxially arranged with the turbine shaft and a brush wire conversion device arranged in the electrical lead; the switching shaft group comprises a switching shaft and a floating connecting shaft which are coaxially arranged; the first end of the transfer shaft is arranged in the output end of the turbine shaft in an interference manner along the axial direction; two ends of the floating connecting shaft are respectively and movably connected with the second end of the switching shaft and the power supply.
Further, the mounting seat assembly comprises a bearing seat for mounting the turbine shaft and a mounting seat for mounting the electrical starter; the bearing seat is fixed with the mounting case, and the turbine disc, the turbine shaft and the adapter shaft are respectively hermetically arranged on the bearing seat; the mounting seat is sleeved outside the floating connecting shaft and the electrical conducting device, a first end of the mounting seat is fixed with the bearing seat, a second end opposite to the first end is fixedly connected with the electrical conducting device, and a second end of the air-entraining cooling tube group is hermetically connected with the mounting seat.
Furthermore, the mounting seat comprises an inner shaft cylinder and an outer shaft cylinder which are sleeved inside and outside, and first ends of the inner shaft cylinder and the outer shaft cylinder are connected to form a closed end fixed with the bearing seat; the floating connecting shaft and the electric leading device are both positioned in the inner shaft barrel, and the electric leading device is fixed with the inner shaft barrel.
Further, the air-entraining cooling pipe group comprises an inner air-entraining pipe and an outer air-entraining pipe which are sleeved inside and outside; the inner air guide pipe is sleeved outside the stress measuring device, the first end of the inner air guide pipe is closed and communicated with a cold air supply source, and the opposite second end of the inner air guide pipe is inserted into the outer shaft cylinder along the axial direction and then fixed with the closed end of the mounting seat, so that a cold air inner flow passage is formed outside the inner shaft cylinder and the stress measuring device; the first end of the outer air guide pipe is connected with the inner air guide pipe in a sealing way and is communicated with the cold air supply source, and the opposite second end of the outer air guide pipe is fixed with the opening end of the outer shaft cylinder in a sealing way so as to form a cold air outer flow passage outside the inner shaft cylinder.
Furthermore, the outer bleed air pipe comprises an outer hollow pipe body with two communicated ends and a first sealing seat connected to the first end of the outer pipe body in a sealing manner; the outer tube body comprises a first horizontal tube coaxially arranged with the stress measuring device and a first vertical tube vertically communicated with the first horizontal tube, an outer mounting edge of an opening of the first horizontal tube is fixed with an inner mounting edge of an opening of the outer tube, and a cold air outlet for cold air to flow out is formed in the joint of the outer tube and the outer tube; the first vertical pipe is provided with a first cold air inlet communicated with a cold air supply source.
Furthermore, the inner air guide pipe comprises an inner pipe body with two communicated and hollow ends and a second sealing seat connected to the first end of the inner pipe body in a sealing manner; the inner pipe body comprises a second horizontal pipe and a second vertical pipe, the second horizontal pipe is coaxially arranged with the first horizontal pipe, the second vertical pipe is vertically communicated with the second horizontal pipe, and after the second horizontal pipe is axially inserted into the outer shaft barrel, the outer installation edge of the second horizontal pipe is fixed with the closed end of the installation seat; the second vertical pipe extends out of the first vertical pipe along the axial direction, and a second cold air inlet communicated with a cold air supply source is formed in the extending end of the second vertical pipe.
Furthermore, the bleed air cooling pipe group also comprises an inner sleeve which is sleeved outside the second horizontal pipe and is positioned in the outer shaft cylinder; the first end of the inner sleeve is abutted against the closed end of the mounting seat, the outer mounting edge of the inner sleeve relative to the second end is fixed between the inner mounting edge of the open end of the outer shaft cylinder and the outer mounting edge of the second end of the outer air guide pipe, and the cold air outlet penetrates through the joint of the inner mounting edge, the outer mounting edge and the inner mounting edge; the inner sleeve and the outer sleeve are matched to form an exhaust ring cavity, and the cold air outer flow channel is communicated with the exhaust ring cavity through a first communication port formed in the inner sleeve.
Furthermore, the measurement supply line group comprises a stress test line connected with a strain gauge attached to the working blade, a cavity temperature and cavity pressure test line used for measuring the cavity temperature and the cavity pressure inside and outside a bearing cavity in the bearing seat, a stress test output line group formed by binding a plurality of stress test output lines, a cooling liquid pipe used for supplying cooling liquid to the stress measurement device, and an oil pipe used for supplying lubricating oil to the stress measurement device; the cavity temperature and cavity pressure test line, the stress test output line group, the cooling liquid pipe and the oil pipe are gathered in the second vertical pipe, penetrate through the second sealing seat along the axial direction of the second vertical pipe and then extend outwards.
Furthermore, the second sealing seat is plate-shaped and is sealed and fixed with the outer mounting edge of the first end of the inner air guide pipe; the inner end face of the second sealing seat is provided with a plurality of mounting grooves communicated with the outside, and the cavity temperature cavity pressure test line, the stress test output line group, the cooling liquid pipe and the oil pipe are sealed to penetrate through the corresponding mounting grooves and then extend out.
The invention has the following beneficial effects:
the invention designs a dynamic stress measuring structure of a blade with a stress measuring device arranged at the rear part and a cooling channel, which can measure the dynamic stress of the blade at the rear end of a turbine of an engine, thereby effectively avoiding the situation that the stress measuring device is inconvenient to arrange when a speed reducer or an accessory transmission device exists at the front end of the engine, and meeting the situation that the stress measuring device is not suitable for being arranged at the front part for measuring the dynamic stress; the engine is provided with a measuring structure, the measuring structure comprises a front end speed reducer and an accessory transmission device, the front end speed reducer and the accessory transmission device are arranged on the engine, and the measuring structure comprises a measuring part and a measuring part; on the other hand, the stress measuring device has strict requirements on the working environment, the temperature of the working environment needs to be below 80 ℃, and when the stress measuring device is arranged at the rear part of the stress measuring device, the temperature of the turbine part of the engine is very high, so that the structure of the invention is provided with the air-entraining cooling pipe group to introduce cooling gas, thereby effectively reducing the influence of the high temperature of the fuel gas at the outlet of the engine on the stress measuring device, ensuring that the temperature of the working environment of the turbine shaft, the adapter shaft group and the stress measuring device is below 80 ℃, and solving the problem of overhigh temperature when the stress measuring device is arranged at the rear part; in the structure of the invention, the measurement supply line group is led out from the first end of the bleed air cooling pipe group, is far away from the upper flow channel and the lower flow channel and is mutually isolated, thereby effectively avoiding forming a new excitation source, influencing the blade dynamic stress measurement and ensuring the validity of test data.
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 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 diagram of a leading dynamic stress test scheme of an electrical lead;
FIG. 2 is a schematic view of a blade dynamic stress measurement configuration of a preferred embodiment of the present invention;
FIG. 3 is a schematic diagram of a set of measurement supply lines for the blade dynamic stress measurement configuration of FIG. 2;
FIG. 4 is a schematic view of a cold air flow path of the blade dynamic stress measurement configuration of FIG. 2;
FIG. 5 is a schematic view showing a spatial structure of the floating connecting shaft of FIG. 2;
FIG. 6 is a schematic space structure diagram of the first seal seat in FIG. 2;
fig. 7 is a schematic space structure diagram of the second seal holder in fig. 2.
Description of the figures
11. A working blade; 12. a turbine disk; 13. an upper flow passage; 14. a lower runner; 20. a turbine shaft; 31. an electricity leading device; 32. a brush wire conversion device; 40. a switching shaft group; 41. a transfer shaft; 411. sealing the labyrinth; 42. a floating connecting shaft; 50. a mounting seat assembly; 51. a bearing seat; 52. a mounting seat; 521. an inner shaft cylinder; 522. an outer shaft barrel; 60. a bleed air cooling tube bank; 601. a cold air inner flow passage; 602. a cold air outer flow passage; 603. a cold air outlet; 604. a first cold air inlet; 605. a second cold air inlet; 606. an exhaust ring cavity; 607. a first communication port; 61. an inner air guiding pipe; 611. an inner tube body; 612. a second seal seat; 6120. mounting grooves; 62. an outer bleed duct; 621. an outer tubular body; 622. a first seal seat; 63. an inner sleeve; 70. measuring the supply line group; 71. a stress test line; 72. a cavity temperature and cavity pressure test line; 73. a stress test output line set; 74. a coolant tube; 75. and (4) an oil pipe.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
Referring to fig. 2 to 4, a preferred embodiment of the present invention provides a blade dynamic stress measuring structure including: the turbine shaft assembly comprises a turbine shaft 20 for mounting a turbine disc 12 with working blades 11, a stress measuring device for measuring the dynamic stress of the blades, a transfer shaft group 40 for performing transfer, and a mounting seat assembly 50 for performing mounting and supporting functions, wherein the output end of the turbine shaft 20 is arranged at an interval with the stress measuring device, two ends of the transfer shaft group 40 are respectively connected with the turbine shaft 20 and the stress measuring device, and the turbine shaft 20, the transfer shaft group 40 and the stress measuring device are respectively arranged in the mounting seat assembly 50. The stress measuring device is further sleeved with a bleed air cooling tube set 60 for introducing external cold air, a first end of the bleed air cooling tube set 60 is closed and is communicated with a cold air supply source for supplying the external cold air, and a second end opposite to the bleed air cooling tube set 60 is hermetically connected with the mounting seat assembly 50 to form a closed cover, so that the introduced cold air cools the turbine shaft 20, the adapting shaft set 40 and the stress measuring device. And a measuring supply line group 70 arranged in the enclosure, the measuring supply line group 70 being used for measuring dynamic stress of the working blade 11, internal and external temperature and pressure of a bearing cavity formed in the mount assembly 50, respectively, and for supplying cooling liquid and lubricating oil to the stress measuring device, the measuring supply line group 70 extending along the bleed air cooling line group 60 and then extending outwardly from the first end of the bleed air cooling line group 60.
The invention designs a dynamic stress measuring structure of a blade with a stress measuring device arranged at the rear part and a cooling channel, which can measure the dynamic stress of the blade at the rear end of a turbine of an engine, thereby effectively avoiding the situation that the stress measuring device is inconvenient to arrange when a speed reducer or an accessory transmission device exists at the front end of the engine, and meeting the situation that the stress measuring device is not suitable for being arranged at the front part for measuring the dynamic stress; the engine is provided with a measuring structure, the measuring structure comprises a front end speed reducer and an accessory transmission device, the front end speed reducer and the accessory transmission device are arranged on the engine, and the measuring structure comprises a measuring part and a measuring part; on the other hand, the stress measuring device has strict requirements on the working environment, the temperature of the working environment needs to be below 80 ℃, and when the stress measuring device is arranged at the rear part of the stress measuring device, the temperature of the turbine part of the engine is very high, so that the structure of the invention is provided with the air-entraining cooling pipe group 60 to introduce cooling gas, thereby effectively reducing the influence of the high temperature of the fuel gas at the outlet of the engine on the stress measuring device, ensuring that the temperature of the working environment of the turbine shaft 20, the adapting shaft group 40 and the stress measuring device is below 80 ℃, and solving the problem of overhigh temperature when the stress measuring device is arranged at the rear part of the stress measuring device; in the structure of the invention, the measurement supply line group 70 is led out from the first end of the bleed air cooling pipe group 60, and is far away from and isolated from the upper flow channel 13 and the lower flow channel 14, so that the influence on the blade dynamic stress measurement caused by the formation of a new excitation source can be effectively avoided, and the validity of test data is ensured.
Alternatively, as shown in fig. 2, the stress measuring device includes an electrical lead 31 disposed coaxially with the turbine shaft 20, and a brush wire switching device 32 disposed inside the electrical lead 31. The adapter shaft group 40 includes an adapter shaft 41 and a floating connection shaft 42 which are coaxially disposed. The first end of the transfer shaft 41 is arranged in the output end of the turbine shaft 20 in an interference manner along the axial direction, the outer circle of the second end of the transfer shaft 41 is provided with a sealing labyrinth 411 extending along the axial direction, the sealing labyrinth 411 and the mounting seat assembly 50 are matched to form a bearing cavity for sealing lubricating oil, and the transfer shaft 41 is simple in structure and easy to process and manufacture. Two ends of the floating connecting shaft 42 are respectively movably connected with the second end of the transfer shaft 41 and the electrical starter 31. In this alternative, as shown in fig. 2 and 5, the floating connecting shaft 42 includes a hollow tube and hexagonal heads connected to two ends of the hollow tube, six sides of the hexagonal heads are spherical sides, the floating connecting shaft 42 is respectively embedded into the second end of the adapting shaft 41 and the electrical initiator 31 through the hexagonal heads at two ends of the floating connecting shaft for effectively compensating the non-concentric condition in the installation or working process of the electrical initiator 31 and the adapting shaft 41, and the influence on the test due to the too large vibration caused by the non-concentricity of the rotor is avoided, and the floating connecting shaft 42 is simple in structure and easy to process and manufacture.
Alternatively, as shown in fig. 2, the mount assembly 50 includes a bearing seat 51 for mounting the turbine shaft 20, and a mount 52 for mounting the electrical lead 31. The bearing seat 51 is fixed with the mounting case, and the turbine disc 12, the turbine shaft 20 and the transfer shaft 41 are respectively and hermetically mounted on the bearing seat 51. The mounting seat 52 is sleeved outside the floating connecting shaft 42 and the electrical conducting device 31, a first end of the mounting seat 52 is fixed with the bearing seat 51, a second end opposite to the first end is fixedly connected with the electrical conducting device 31, and a second end of the bleed air cooling tube group 60 is connected with the mounting seat 52 in a sealing mode. In the alternative, the mounting seat 52 is circumferentially perforated according to the original mounting hole of the bearing seat 51 and is fixed with the bearing seat 51 through bolt connection; the outer mounting edge of the electrical starter 31 and the mounting seat 52 are also detachably fixed through bolts; the bleed air cooling tube bank 60 is also removably secured to the mounting block 52 by an outer mounting edge.
In this alternative, as shown in fig. 2, the mounting seat 52 includes an inner shaft tube 521 and an outer shaft tube 522 that are sleeved inside and outside, first ends of the inner shaft tube 521 and the outer shaft tube 522 are connected to form a closed end fixed to the bearing seat 51, and a bolt is inserted through the first ends of the inner shaft tube 521 and the outer shaft tube 522 and the bearing seat 51 to fixedly connect the three into a whole. The floating connecting shaft 42 and the electrical starter 31 are both positioned in the inner shaft barrel 521, and the electrical starter 31 is fixed with the inner shaft barrel 521. The mounting seat 52 has a simple structure and is easy to manufacture, and comprises an inner shaft barrel 521 and an outer shaft barrel 522 which are sleeved inside and outside, so that the flow of subsequent cold air is facilitated.
Optionally, as shown in figures 2 and 4, the bleed air cooling tube bank 60 includes inner and outer bleed air tubes 61 and 62 that are telescopically arranged. The inner air guiding pipe 61 is sleeved outside the stress measuring device, a first end of the inner air guiding pipe is closed and communicated with the cold air supply source, and a second end of the inner air guiding pipe is inserted into the outer shaft cylinder 522 along the axial direction and then fixed with the closed end of the mounting seat 52, so that a cold air inner flow passage 601 is formed outside the inner shaft cylinder 521 and the stress measuring device. A first end of the outer bleed air duct 62 is sealingly connected to the inner bleed air duct 61 and communicates with the cool air supply source, and an opposite second end thereof is sealingly fixed to an open end of the outer cylinder 522 to form a cool air outer flow passage 602 outside the inner cylinder 521.
In this alternative, as shown in fig. 4, the outer bleed air pipe 62 includes an outer pipe 621 with two ends connected and hollow, and a first sealing seat 622 sealingly connected to the first end of the outer pipe 621. Outer body 621 includes the first horizontal pipe with the coaxial setting of stress measurement device, and with the first vertical pipe of the perpendicular intercommunication of first horizontal pipe, the limit is installed fixedly in the open-ended outer installation limit of first horizontal pipe and outer bobbin 522, and the junction between them offers the outside cold air export 603 that supplies the cold air to flow out. The first vertical pipe is opened with a first cold air inlet 604 communicating with a cold air supply source.
In this alternative, as shown in fig. 4, the inner gas guiding pipe 61 includes an inner pipe 611 having two ends connected and hollow, and a second sealing seat 612 connected to the first end of the inner pipe 611 in a sealing manner. The inner tube 611 includes a second horizontal tube coaxially disposed with the first horizontal tube, and a second vertical tube vertically connected to the second horizontal tube, and after the second horizontal tube is axially inserted into the outer shaft 522, its outer mounting edge is fixed to the closed end of the mounting seat 52. The second vertical pipe extends out of the first vertical pipe along the axial direction, and the extending end of the second vertical pipe is provided with a second cold air inlet 605 communicated with the cold air supply source.
Further, as shown in fig. 4, the bleed air cooling tube bank 60 further includes an inner sleeve 63 sleeved outside the second horizontal tube and located inside the outer sleeve 522. The inner sleeve 63 has a first end abutting the closed end of the mounting block 52 and an outer mounting edge opposite the second end secured between the inner mounting edge of the open end of the outer sleeve 522 and the outer mounting edge of the second end of the outer bleed air duct 62, with the cold air outlet 603 extending through the junction of the three. The inner sleeve 63 and the outer sleeve 522 are matched to form an exhaust annular chamber 606, and the cold air flow passage 602 is communicated with the exhaust annular chamber 606 through a first communication port 607 formed in the inner sleeve 63.
During operation, the cold air supplied by the cold air supply source enters the outer bleed air pipe 62 through the first cold air inlet 604, forms a cold air outer flow passage 602 between the outer bleed air pipe 62 and the inner bleed air pipe 61, enters the exhaust annular cavity 606 between the inner sleeve 63 and the outer sleeve 522 through the first communication ports 607 arranged on the inner sleeve 63 at intervals in the circumferential direction, and is exhausted outside through the cold air outlet 603 penetrating through the outer sleeve 522, the inner sleeve 63 and the outer bleed air pipe 62. Meanwhile, the cold air supplied by the cold air supply source enters the inner air guiding pipe 61 through the second cold air inlet 605, and then enters the inner shaft cylinder 521 through a circumferential annular hole on the inner shaft cylinder 521, at this time, the flow path is divided into three paths, one path enters the switching shaft 41 and the turbine shaft 20 from a small hole processed on the switching shaft 41, and the measurement supply line group 70 in the two paths is cooled, so that the measurement supply line group 70 is prevented from being damaged due to high temperature; a flow of lubricating oil flows from the gap between the sealing labyrinth 411 on the adapter shaft 41 and the bearing seat 51 and is used for sealing the bearing cavity to prevent the lubricating oil from leaking; an internal passage is formed through the closed end of the mounting block 52 into the exhaust annulus 606 and out through the cold air outlet 603.
Alternatively, as shown in fig. 2 and 3, the measurement supply line group 70 includes a stress test line 71 for connecting to a strain gauge attached to the rotor blade 11, a cavity temperature and cavity pressure test line 72 for measuring the cavity temperature and cavity pressure of the bearing cavity in the bearing housing 51, a stress test output line group 73 formed by binding a plurality of stress test output lines, a cooling liquid pipe 74 for supplying cooling liquid to the stress measuring device, and an oil pipe 75 for supplying lubricating oil to the stress measuring device. The cavity temperature and cavity pressure test line 72, the stress test output line set 73, the cooling liquid pipe 74 and the oil pipe 75 are collected in the second vertical pipe, and extend outwards after penetrating through the second seal seat 612 along the axial direction of the second vertical pipe. As shown in fig. 3, first, the stress test line 71 connected to the strain gauge adhered to the surface of the working blade 11 is converted into a stress test output line group 73 formed by binding a plurality of stress test output lines through the surface of the working blade 11, the inside of the turbine shaft 20, the inside of the adapter shaft 41, the inside of the floating connecting shaft 42, the inside of the electrical initiator 31, the brush wire conversion device 32, and finally led out by the second seal seat 612; secondly, in the working process of the electrical lead 31, besides the control of the external environment temperature, the cooling liquid needs to be added for cooling inside the electrical lead 31, and meanwhile, lubricating oil needs to be added for lubrication, so that the cooling liquid pipe 74 and the oil pipe 75 connected with the electrical lead 31 are led out from the tail of the electrical lead 31 and then led out through the second sealing seat 612; finally, the structure of the invention arranges a cavity temperature and cavity pressure test line 72 inside and outside the bearing cavity, on one hand, the pressure inside and outside the bearing cavity and the cavity temperature are respectively monitored in real time in the test process, so that the pressure inside the bearing cavity is prevented from being larger than the pressure outside the bearing cavity, the lubricating oil is prevented from leaking from the position of the sealing labyrinth 411 of the adapter shaft 41, and the working environment temperature of the electricity leading device 31 is prevented from being overhigh, on the other hand, if the pressure outside the bearing cavity is slightly small and the temperature is slightly high in the monitoring process, the air inflow of the cold air can be adjusted in real time to adjust, so that the pressure and the temperature are ensured to be in reasonable ranges, and the lubricating oil is prevented from leaking and the working environment temperature of the electricity leading device 31 is prevented from being overhigh.
Optionally, as shown in fig. 6, the first sealing seat 622 is a half-round structure, and is "hooped" with the inner air guiding pipe 61, and is fixed to the outer air guiding pipe 62 by a bolt, and the half-round joint is sealed by gluing, which effectively reduces the leakage of the cool air in the cool air outer flow passage 602 from the seam.
Alternatively, as shown in fig. 7, the second sealing seat 612 is plate-shaped and is fixed to the outer mounting edge of the first end of the inner air guiding pipe 61 in a sealing manner. The inner end surface of the second sealing seat 612 is provided with a plurality of mounting grooves 6120 communicated with the outside, and the cavity temperature and cavity pressure test line 72, the stress test output line group 73, the cooling liquid pipe 74 and the oil pipe 75 are hermetically inserted into the corresponding mounting grooves 6120 and then extend out. The second sealing seat 612 is of a circumferential slotted structure, the cavity temperature and cavity pressure test line 72, the oil pipe 75, the cooling liquid pipe 74 and the stress test output line group 73 with different specifications are led out from the mounting groove 6120 with corresponding size, the upper end surface of the second sealing seat 612 is coated with sealant, and then the second sealing seat is connected and fixed with the inner air guide pipe 61 through bolts, so that cold air leakage at the position can be effectively reduced.
In the structure of the invention, two groups of sealing seats (a first sealing seat 622 and a second sealing seat 612) are designed, the structure is simple, the sealing effect can be achieved by simply gluing and sealing during installation, wherein the second sealing seat 612 is designed with different mounting groove structures, compared with the structure that a large hole is directly opened for leading out after a leading-out pipeline and a test line are bound, the cold air leakage can be greatly reduced.
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 (10)
1. A blade dynamic stress measurement structure, comprising:
the stress measuring device comprises a turbine shaft (20) used for mounting a turbine disc (12) with working blades (11), a stress measuring device used for measuring the dynamic stress of the blades, a switching shaft group (40) having a switching function and a mounting seat assembly (50) having a mounting and supporting function, wherein the output end of the turbine shaft (20) is arranged at an interval with the stress measuring device, two ends of the switching shaft group (40) are respectively connected with the turbine shaft (20) and the stress measuring device, and the turbine shaft (20), the switching shaft group (40) and the stress measuring device are respectively arranged in the mounting seat assembly (50);
a bleed air cooling pipe set (60) for introducing external cold air is sleeved outside the stress measuring device, a first end of the bleed air cooling pipe set (60) is closed and is communicated with a cold air supply source for supplying the external cold air, and a second end opposite to the bleed air cooling pipe set is hermetically connected with the mounting seat assembly (50) to form a closed cover, so that the introduced cold air cools the turbine shaft (20), the adapting shaft set (40) and the stress measuring device;
the device also comprises a measuring supply line group (70) arranged in the closed cover, wherein the measuring supply line group (70) is used for respectively measuring the dynamic stress of the working blade (11), the internal and external temperature and pressure of a bearing cavity formed in the mounting seat assembly (50), and supplying cooling liquid and lubricating oil to the stress measuring device, and the measuring supply line group (70) extends along the bleed air cooling pipe group (60) and then extends outwards from the first end of the bleed air cooling pipe group (60).
2. Blade dynamic stress measurement structure according to claim 1,
the stress measuring device comprises an electrical starter (31) and a brush wire conversion device (32), wherein the electrical starter (31) is coaxially arranged with the turbine shaft (20), and the brush wire conversion device (32) is arranged in the electrical starter (31);
the adapter shaft group (40) comprises an adapter shaft (41) and a floating connecting shaft (42) which are coaxially arranged;
the first end of the transfer shaft (41) is arranged in the output end of the turbine shaft (20) in an interference manner along the axial direction;
two ends of the floating connecting shaft (42) are respectively and movably connected with the second end of the transfer connecting shaft (41) and the electric starter (31).
3. Blade dynamic stress measurement structure according to claim 2,
the mounting seat assembly (50) comprises a bearing seat (51) for mounting the turbine shaft (20) and a mounting seat (52) for mounting the electrical starter (31);
the bearing seat (51) is fixed with the mounting casing, and the turbine disc (12), the turbine shaft (20) and the transfer shaft (41) are respectively and hermetically arranged on the bearing seat (51);
the mounting seat (52) is sleeved outside the floating connecting shaft (42) and the electric initiator (31), a first end of the mounting seat (52) is fixed with the bearing seat (51), a second end opposite to the first end is fixedly connected with the electric initiator (31), and a second end of the bleed air cooling pipe group (60) is connected with the mounting seat (52) in a sealing mode.
4. Blade dynamic stress measurement structure according to claim 3,
the mounting seat (52) comprises an inner shaft cylinder (521) and an outer shaft cylinder (522) which are sleeved inside and outside, and first ends of the inner shaft cylinder (521) and the outer shaft cylinder (522) are connected to form a closed end fixed with the bearing seat (51);
the floating connecting shaft (42) and the electric initiator (31) are both positioned in the inner shaft cylinder (521), and the electric initiator (31) is fixed with the inner shaft cylinder (521).
5. Blade dynamic stress measurement structure according to claim 4,
the bleed air cooling pipe group (60) comprises an inner bleed air pipe (61) and an outer bleed air pipe (62) which are sleeved with each other;
the inner air guide pipe (61) is sleeved outside the stress measuring device, the first end of the inner air guide pipe is closed and communicated with the cold air supply source, and the opposite second end of the inner air guide pipe is inserted into the outer shaft cylinder (522) along the axial direction and then fixed with the closed end of the mounting seat (52) so as to form a cold air inner flow passage (601) outside the inner shaft cylinder (521) and the stress measuring device;
the first end of the outer air guide pipe (62) is connected with the inner air guide pipe (61) in a sealing mode and is communicated with the cold air supply source, and the opposite second end of the outer air guide pipe is fixedly connected with the open end of the outer shaft cylinder (522) in a sealing mode, so that a cold air outer flow channel (602) is formed outside the inner shaft cylinder (521).
6. Blade dynamic stress measurement structure according to claim 5,
the outer bleed air pipe (62) comprises an outer pipe body (621) with two communicated ends and a hollow, and a first sealing seat (622) connected to the first end of the outer pipe body (621) in a sealing mode;
the outer tube body (621) comprises a first horizontal tube coaxially arranged with the stress measuring device and a first vertical tube vertically communicated with the first horizontal tube, an outer mounting edge of an opening of the first horizontal tube is fixed with an inner mounting edge of an opening of the outer shaft tube (522), and a cold air outlet (603) for cold air to flow out is formed in the joint of the outer tube body and the outer tube body;
the first vertical pipe is provided with a first cold air inlet (604) communicated with the cold air supply source.
7. Blade dynamic stress measurement structure according to claim 6,
the inner air guide pipe (61) comprises an inner pipe body (611) with two communicated ends and a hollow inner pipe body, and a second sealing seat (612) connected to the first end of the inner pipe body (611) in a sealing mode;
the inner pipe body (611) comprises a second horizontal pipe and a second vertical pipe, the second horizontal pipe is coaxially arranged with the first horizontal pipe, the second vertical pipe is vertically communicated with the second horizontal pipe, and after the second horizontal pipe is axially inserted into the outer shaft cylinder (522), the outer installation edge of the second horizontal pipe is fixed with the closed end of the installation seat (52);
the second vertical pipe extends out of the first vertical pipe along the axial direction, and a second cold air inlet (605) communicated with the cold air supply source is formed in the extending end of the second vertical pipe.
8. Blade dynamic stress measurement structure according to claim 7,
the bleed air cooling pipe group (60) further comprises an inner sleeve (63) sleeved outside the second horizontal pipe and positioned in the outer shaft cylinder (522);
the first end of the inner sleeve (63) is abutted against the closed end of the mounting seat (52), the outer mounting edge of the inner sleeve opposite to the second end is fixed between the inner mounting edge of the open end of the outer shaft sleeve (522) and the outer mounting edge of the second end of the outer bleed air pipe (62), and the cold air outlet (603) penetrates through the joint of the inner mounting edge, the outer mounting edge and the inner mounting edge;
inner sleeve (63) with outer shaft tube (522) cooperation forms exhaust ring chamber (606), just cold air runner (602) through set up in first intercommunication mouth (607) on inner sleeve (63) with exhaust ring chamber (606) intercommunication.
9. Blade dynamic stress measurement structure according to claim 8,
the measuring supply line group (70) comprises a stress test line (71) connected with a strain gauge attached to the working blade (11), a cavity temperature and cavity pressure test line (72) used for measuring the inner cavity and the outer cavity of a bearing cavity in the bearing seat (51) and the cavity pressure, a stress test output line group (73) formed by binding a plurality of stress test output lines, a cooling liquid pipe (74) used for supplying cooling liquid to the stress measuring device, and an oil pipe (75) used for supplying lubricating oil to the stress measuring device;
the cavity temperature and cavity pressure test line (72), the stress test output line group (73), the cooling liquid pipe (74) and the oil pipe (75) are collected in the second vertical pipe, penetrate through the second sealing seat (612) along the axial direction of the second vertical pipe and then extend outwards.
10. Blade dynamic stress measurement structure according to claim 9,
the second sealing seat (612) is plate-shaped and is sealed and fixed with the outer mounting edge of the first end of the inner air guide pipe (61);
the inner end face of the second sealing seat (612) is provided with a plurality of mounting grooves (6120) communicated with the outside, and the cavity temperature and cavity pressure test line (72), the stress test output line group (73), the cooling liquid pipe (74) and the oil pipe (75) are hermetically inserted into the corresponding mounting grooves (6120) and then extend out.
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