CN113153439B - Compact turbine shaft structure with torsion measuring function - Google Patents
Compact turbine shaft structure with torsion measuring function Download PDFInfo
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- CN113153439B CN113153439B CN202110491445.4A CN202110491445A CN113153439B CN 113153439 B CN113153439 B CN 113153439B CN 202110491445 A CN202110491445 A CN 202110491445A CN 113153439 B CN113153439 B CN 113153439B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L3/00—Measuring torque, work, mechanical power, or mechanical efficiency, in general
- G01L3/02—Rotary-transmission dynamometers
- G01L3/04—Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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- General Physics & Mathematics (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses a compact turbine shaft structure with a torque measuring function, which relates to the technical field of turbine engines and comprises a power turbine shaft, a torque measuring device and a torque measuring device, wherein the power turbine shaft comprises a power input end, a power output end and a thin shaft; the reinforcing ribs are uniformly arranged on the outer peripheral wall of the thin shaft; the reference shaft is integrally sleeved on the power turbine shaft; the invention relates to the technical field of turbine engines, in particular to a torque measuring ring which is suitable for being assembled on a power output end and is matched with a reference shaft for use to measure torque. The compact turbine shaft structure with the torsion measuring function has enough bending resistance while realizing the torsion measuring function of the compact turbine shaft through the arranged thin shaft and the reinforcing ribs on the surface of the thin shaft; through the benchmark axle that sets up, include thin axle and strengthening rib completely in inside, avoid the power turbine shaft directly to expose in the oil gas environment, reduce the strengthening rib friction, weaken the blast air effect that the strengthening rib brought, avoid the blast air loss.
Description
Technical Field
The invention belongs to the technical field of turbine engines, and particularly relates to a compact turbine shaft structure with a torsion measuring function.
Background
The turbine shaft is an important part of a turbine engine and is only a simple metal pipe, but actually, the turbine shaft is a precision part with 120000-160000 rpm rotation and ultrahigh temperature, and the fine machining tolerance and deep material application and treatment are the most central technologies of all turbine factories. At present, an aviation turboshaft engine is usually provided with a torque measuring structure on a turbine shaft in the engine to monitor the instantaneous torque of the engine, and the torque measuring principle is usually an electric phase method.
The specific principle of the electric phase method is that a reference shaft is arranged outside or inside a power turbine shaft, one end of the reference shaft is connected with the power turbine shaft through a pin, the reference shaft at the end is guaranteed to be always consistent with the circumferential displacement of the power turbine shaft, and a torque measuring ring is arranged at the other end of the reference shaft (the reference shaft is in large radial clearance fit with the power turbine shaft and is guaranteed to rotate freely and not limited by the power turbine shaft), and is also connected with the power turbine shaft through the pin, so that the torque measuring ring is always consistent with the circumferential displacement of the power turbine shaft. In the working process of the engine, the working blades of the power turbine directly transmit the work of gas expansion to the power turbine shaft, the power turbine shaft generates torque, when the power turbine shaft bears the torque, different circumferential displacements occur at different axial positions, namely, different circumferential displacements occur at the positions of two ends of the power turbine shaft, one end of the reference shaft is connected with the power turbine shaft through a pin, the other end of the reference shaft is in large radial clearance fit with the power turbine shaft and is not influenced by the power turbine shaft, so that the circumferential displacements at the joint of the reference shaft and a left-end pin are the same, the circumferential displacements at the joint of the torsion measuring ring and a right-end pin are the same, when the engine works, the circumferential displacement at the joint of the left-end pin and the right-end pin has displacement difference, the larger the torque borne by the power turbine shaft is, the larger the torque difference is, the contained angle between the tooth of reference shaft and survey torsion bar will change, torque sensor passes through the reference shaft and surveys the cutting magnetic induction line perception reference shaft of torsion bar and the phase place and the frequency of surveying the torsion bar, along with the continuous grow of moment of torsion, the reference shaft will change with the contained angle of surveying the torsion bar, the change of contained angle will be directly through the change perception of phase angle by torque sensor, torque sensor passes through the change of phase angle and comes the instantaneous moment of torsion of perception power turbine shaft, thereby obtain the instantaneous power of engine, the above-mentioned fundamental principle who twists is surveyed for electric phase place promptly.
Most of the power turbines can adopt electric phase torque measurement to be front output engines, the front output engines are usually long, meanwhile, in order to consider that the power turbine shafts can penetrate through the core part of the gas generator, the outer diameters of the shafts are usually not large, the torsional rigidity of the shafts is not large, a large torsion angle can be realized under the design power of the engines, and good torque measurement precision can be guaranteed. However, the current aviation turboshaft engine is developing towards compact type, for the engine outputting power after, the span of the power turboshaft is usually short, and is limited by the structure of the engine, the power turboshaft rotor is mostly a cantilever rotor, in order to meet the requirement that the power turboshaft gripping force smoothly passes through the critical rotating speed, at this time, the turboshaft is often required to have larger bending rigidity, namely, the outer diameter of the shaft is large enough, and the outer diameter of the turboshaft is too large, which will cause the torsional rigidity of the shaft to be also large, thereby causing the torsion angle to be too small, the accuracy of the too small torsion angle is usually lower, and the practical engineering meaning is not large, so under this condition, the turboshaft engine cannot measure the torsion inside the engine.
Therefore, the person skilled in the art provides a compact turbine shaft structure with torque measurement function to solve the problems mentioned in the background art.
Disclosure of Invention
The present invention is directed to a compact turbine shaft structure with torque measurement to address at least one of the problems and disadvantages set forth in the background of the invention.
According to one aspect of the invention, a compact turbine shaft structure with a torque measurement function is provided, and the compact turbine shaft structure comprises: the device comprises a power turbine shaft, a power output end and a power output end, wherein one end of the power turbine shaft is a power input end, the other end of the power turbine shaft is a power output end, and a thin shaft is arranged between the power input end and the power output end; the reinforcing ribs are arranged and are uniformly arranged on the outer peripheral wall of the thin shaft; a reference shaft having one end adapted to be fitted on the power input end and the other end adapted to be fitted on the power output end; and the torsion measuring ring is suitable for being assembled on the power output end and is matched with the reference shaft for use to measure torque.
According to an exemplary embodiment of the invention, a collar is arranged at one end of the power input end close to the thin shaft, and first pin holes are uniformly arranged at the power input end between the collar and the thin shaft; and a shaft shoulder is arranged at one end of the power output end, which is close to the thin shaft, and second pin holes are uniformly formed in the shaft shoulder.
According to another exemplary embodiment of the present invention, the thin shaft may be solid or hollow, and is selected according to actual requirements of the engine.
According to another exemplary embodiment of the invention, the number of the reinforcing ribs is selected as a prime number, and the specific number and the specific size of the reinforcing ribs are calculated and experimentally analyzed according to actual conditions to finally determine the appropriate size; because the reinforcing ribs are not continuous in the circumferential direction, the torsional rigidity of the compact turbine shaft torsion measuring section with the torsion measuring function is mainly borne by the thin shaft, and the reinforcing ribs have small contribution to the torsional rigidity; meanwhile, the structure of the external reinforcing rib is similar to that of an I-beam, the I-beam has higher bending rigidity in the longitudinal section direction, and the problem of insufficient bending resistance of the thin shaft is solved.
According to another exemplary embodiment of the present invention, the axial length of the reference shaft is smaller than the power turbine shaft but larger than the thin shaft, the reference shaft is sleeved on the power turbine shaft, one end of the reference shaft is attached to the vertical surface of the shaft collar, and the other end of the reference shaft is sleeved on the shaft shoulder; one end of the reference shaft, which is close to the shaft collar, is uniformly provided with a reference shaft pin hole, and the other end of the reference shaft is uniformly provided with a first torque measuring tooth.
According to another exemplary embodiment of the present invention, the end of the reference shaft near the collar is in transition fit with the power turbine shaft, and the relative rotation between the end of the reference shaft near the collar and the power turbine shaft is limited; the other end of the reference shaft is in clearance fit with the shaft shoulder, so that the reference shaft can smoothly rotate on the shaft shoulder, and the reference shaft and the torsion measuring ring can be matched for use to realize torsion measuring function.
According to another exemplary embodiment of the present invention, the reference shaft pin hole is arranged in correspondence with the first pin hole, both cooperating with the first pin for limiting the axial displacement of the reference shaft on the power turbine shaft.
According to another exemplary embodiment of the present invention, the torsion measuring ring is sleeved on the shaft shoulder, the torsion measuring ring is uniformly provided with torsion measuring ring pin holes, and one end of the torsion measuring ring is uniformly provided with second torsion measuring teeth.
According to another exemplary embodiment of the present invention, the torsion ring pin hole and the second pin hole are correspondingly arranged, and are used in cooperation with the second pin to limit the axial displacement of the torsion ring on the power turbine shaft.
According to another exemplary embodiment of the present invention, the first torque measuring tooth and the second torque measuring tooth form an angle of 90 ° therebetween in the non-operating state.
Compared with the prior art, the invention has the beneficial effects that:
1. the torque measuring function of the compact turbine shaft is realized through the thin shaft and the reinforcing ribs on the surface of the thin shaft, the torsional rigidity of the torque measuring section of the compact turbine shaft with the torque measuring function is mainly borne by the thin shaft due to the fact that the external reinforcing ribs are circumferentially discontinuous, and the contribution of the external reinforcing ribs to the torsional rigidity is small; meanwhile, the structure of the external reinforcing rib is similar to that of an I-beam, the I-beam has higher bending rigidity in the longitudinal section direction, and the problem of insufficient bending resistance of the thin shaft is solved.
2. Through the reference shaft arranged in the invention, the length of the reference shaft is greater than the lengths of the thin shaft and the reinforcing ribs, so that the thin shaft and the reinforcing ribs can be completely contained in the reference shaft, the power turbine shaft is prevented from being directly exposed in an oil-gas environment, the friction of the reinforcing ribs is reduced, the blast effect caused by the reinforcing ribs is eliminated or weakened, and the blast loss is avoided.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is an exploded view of a compact turbine shaft structure with torque measurement function;
FIG. 2 is a schematic view of the overall assembly of a compact turbine shaft structure with torque measurement function;
FIG. 3 is a structural section view of a compact turbine shaft with torque measurement function;
FIG. 4 is a power turbine shaft subjective view;
FIG. 5 is a cross-sectional view of a hollow thin shaft;
FIG. 6 is a cross-sectional view of a solid thin shaft;
FIG. 7 is a schematic illustration of a coarse axis of an experimental turbine;
FIG. 8 is a schematic view of an experimental turbine thin shaft;
FIG. 9 is a cross-sectional view of the torsion ring and reference shaft in a non-operational state;
FIG. 10 is a cross-sectional view of the torsion ring and reference shaft in operation.
In the figure: 1. a power turbine shaft; 101. a power input; 102. a power output end; 103. a thin shaft; 104. Reinforcing ribs; 105. a collar; 106. a shaft shoulder; 107. a first pin hole; 108. a second pin hole; 2. a reference axis; 201. a reference shaft pin hole; 202. a first torque measuring tooth; 3. measuring a torsion ring; 301. measuring a torsion ring pin hole; 302. A second torque measuring tooth; 4. a first pin; 5. a second pin; 6. testing a turbine thick shaft; 7. thin shaft of experimental turbine.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention are further described in detail below by way of examples with reference to the accompanying drawings. In the specification, the same or similar reference numerals denote the same or similar components. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the general inventive concept of the present invention and should not be construed as limiting the invention.
Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in schematic form in order to simplify the drawing.
According to one general technical concept of the present invention, there is provided a compact turbine shaft structure with a torque measurement function, including: one end of the power turbine shaft 1 is a power input end 101, the other end of the power turbine shaft 1 is a power output end 102, and a thin shaft 103 is arranged between the power input end 101 and the power output end 102; a plurality of reinforcing ribs 104 are arranged on the outer peripheral wall of the thin shaft 103; a reference shaft 2 having one end adapted to be fitted on the power input terminal 101 and the other end adapted to be fitted on the power output terminal 102; a torque measuring ring 3, the torque measuring ring 3 being adapted to be fitted on the power take-off 102 for use with the reference shaft 2 for measuring torque.
FIG. 1 is an exploded view of a compact turbine shaft structure with torque measurement function. FIG. 2 is a schematic view of the overall assembly of a compact turbine shaft structure with torque measurement function. Fig. 3 is a structural section view of a compact turbine shaft with a torque measuring function, and fig. 4 is a subjective view of a power turbine shaft.
As shown in fig. 1-4, in the illustrated embodiment, the power input 101 is provided with a collar 105 at an end thereof adjacent to the thin shaft 103, and the power input 101 is provided with first pin holes 107 uniformly between the collar 105 and the thin shaft 103; one end of the power output end 102 close to the thin shaft 103 is provided with a shaft shoulder 106, and the shaft shoulder 106 is uniformly provided with second pin holes 108.
Preferably, as shown in fig. 1 to 4, in actual use, the number of the reinforcing ribs 104 is selected as a prime number, and the specific number and the specific size of the reinforcing ribs 104 are calculated and experimentally analyzed to finally determine a proper size according to actual conditions;
specifically, as the plurality of reinforcing ribs 104 are uniformly distributed on the outer peripheral wall of the thin shaft 103, compared with the traditional cylindrical section turbine shaft, the structure has the problem that the bending rigidity distribution is uneven between two adjacent reinforcing ribs 104, and has certain influence on the dynamic characteristics of the turbine rotor, and analysis shows that if the number of the reinforcing ribs 104 is selected as a prime number, and if 11 positions are uniformly distributed but 10 positions are not selected, the bending section coefficient of the turbine shaft along the two adjacent reinforcing ribs 104 is basically unchanged; meanwhile, the reinforcing ribs 104 are not continuous in the circumferential direction, so that the torsional rigidity of the compact turbine shaft torsion measuring section with the torsion measuring function is mainly borne by the thin shaft 103, the contribution of the reinforcing ribs 104 to the torsional rigidity is small, the structure of the reinforcing ribs 104 is similar to that of an I-beam, the I-beam has high bending rigidity in the longitudinal section direction, and the problem of insufficient bending resistance of the thin shaft 103 is solved.
Preferably, as shown in fig. 1 to 4, in practical use, the axial length of the reference shaft 2 is smaller than that of the power turbine shaft 1 but larger than that of the thin shaft 103, and the thin shaft 103 and the reinforcing ribs 104 can be completely included in the reference shaft 2, so that the power turbine shaft 1 is prevented from being directly exposed to an oil-gas environment, friction of the reinforcing ribs 104 is reduced, a blowing effect caused by the reinforcing ribs 104 is eliminated or weakened, and blowing loss is avoided; the reference shaft 2 is sleeved on the power turbine shaft 1, one end of the reference shaft 2 is attached to the vertical surface of the shaft collar 105, and the other end of the reference shaft 2 is sleeved on the shaft shoulder 106; one end of the reference shaft 2 close to the collar 105 is uniformly provided with a reference shaft pin hole 201, and the other end of the reference shaft 2 is uniformly provided with a first torque measuring tooth 202.
Preferably, as shown in fig. 3, in actual use, one end of the reference shaft 2 close to the collar 105 is in transition fit with the power turbine shaft 1, and the relative rotation between one end of the reference shaft 2 close to the collar 105 and the power turbine shaft 1 is limited; the other end of the reference shaft 2 is in clearance fit with the shaft shoulder 106, so that the reference shaft 2 can smoothly rotate on the shaft shoulder 106, and the reference shaft 2 and the measuring torsion ring 3 can be matched for use to realize the torsion measuring function.
Preferably, as shown in fig. 2, in actual use, the reference shaft pin hole 201 is provided corresponding to the first pin hole 107, and both are used in cooperation with the first pin 4 for restricting the axial displacement of the reference shaft 2 on the power turbine shaft 1.
Preferably, as shown in fig. 1 and fig. 2, in practical use, the torsion measuring ring 3 is sleeved on the shaft shoulder 106, torsion measuring ring pin holes 301 are uniformly formed in the torsion measuring ring 3, and a second torsion measuring tooth 302 is uniformly formed at one end of the torsion measuring ring.
Preferably, as shown in fig. 2, in actual use, the torsion ring pin hole 301 and the second pin hole 108 are correspondingly arranged, and the two are used in cooperation with the second pin 5 for limiting the axial displacement of the torsion ring 3 on the power turbine shaft 1.
Fig. 5 is a cross-sectional view of a hollow thin shaft. Fig. 6 is a solid thin shaft cross-sectional view.
As shown in fig. 5 and 6, in the illustrated embodiment, the thin shaft 103 may be solid or hollow, and is selected according to the actual requirement of the engine.
The above is the description of each part of the compact turbine shaft structure with the torque measuring function; next, the structural feasibility of the compact turbine shaft with the torque measurement function is verified by comparing and analyzing the compact turbine shaft with the experimental turbine thick shaft 6 and the experimental turbine thin shaft 7.
FIG. 7 is a schematic illustration of the experimental turbine coarse axis. FIG. 8 is a schematic view of the experimental turbine thin shaft. Fig. 9 is a sectional view of the torsion ring 3 and the reference shaft in a non-operating state. Fig. 10 is a sectional view showing the operation state of the torsion ring 3 and the reference shaft.
As shown in fig. 7 and 8, in the illustrated embodiment, the outer diameter of the experimental turbine thick shaft 6 is phi 46mm, and the outer diameter of the experimental turbine thin shaft 7 is phi 24 mm; meanwhile, the outer diameter of the reinforcing rib 104 is phi 46mm, and the outer diameter of the inner circle is phi 24 mm.
And (3) carrying out torsion angle calculation on the three shafts, wherein the calculation formula is as follows:
in the formula (I), the compound is shown in the specification,
is a torsion angle; t is torque; l is the length of the torsion section; g is the shear modulus,
is the polar moment of inertia of the cross section; G.IpIs torsional rigidity.
The same torque was applied to the three shafts, respectively, at a torque of 700N · m, and the torsion angles within 193.3mm in axial length of the experimental turbine thick shaft 6, the experimental turbine thin shaft 7, and the turbine shaft of the present invention were calculated. At the moment, the torsion angle of the experimental turbine coarse shaft 6 is 0.3 degrees, the torsion angle of the experimental turbine fine shaft 7 is 3.0 degrees, and the torsion angle of the turbine shaft of the invention is 2.24 degrees.
And (3) carrying out deflection calculation on the three shafts, wherein the calculation formula is as follows:
in the formula, w is deflection; m is a bending moment; e is the modulus of elasticity; i is a section moment of inertia; EI is the bending stiffness.
From (1), it can be seen that the larger the bending stiffness EI, the smaller the deflection w, but for irregular shafts, the bending stiffness EI is often difficult to calculate, so the bending stiffness can be reflected by the deflection w side, and the smaller the deflection, the larger the bending stiffness can be reflected from the side.
In order to simulate the actual working state of a novel compact turbine shaft with a torque measuring function in an engine, the left end and the right end of the three shafts are restrained, the left end is set as a fixed hinge, and a ball bearing is simulated; the right end is designed as an axial slidable hinge to simulate a rod bearing; and applying a shaft pressing force to the middle of the shaft, wherein the shaft pressing force is 1000N. At the moment, the maximum deflection of the experimental turbine thick shaft 6 is 0.011mm, the maximum deflection of the experimental turbine thin shaft 7 is 0.13mm, and the maximum deflection of the turbine shaft is 0.025 mm.
The results of the above calculation analysis show that: 1) the torsion angle of the experimental turbine coarse shaft 6 is 0.1 time of the torsion angle of the experimental turbine fine shaft 7, and the torsion angle of the turbine shaft of the invention is 0.75 time of the torsion angle of the experimental turbine fine shaft 7; 2) the maximum deflection of the experimental turbine fine shaft 7 is only 11.8 times of that of the experimental turbine coarse shaft 6, and the maximum deflection of the turbine shaft of the invention is 2.2 times of that of the experimental turbine coarse shaft 6.
Therefore, the turbine shaft has a certain torsion angle and also has good bending rigidity, and has obvious guiding significance for realizing internal torsion measurement of the compact turboshaft engine.
Meanwhile, as shown in fig. 9 and 10, in the illustrated embodiment, the first torque measuring tooth 202 and the second torque measuring tooth 302 form an included angle of 90 ° therebetween in the non-operating state; when the first torsion measuring gear 202 and the second torsion measuring gear 302 are in a working state, the included angle between the first torsion measuring gear and the second torsion measuring gear changes, so that the torsion measuring function of the compact turbine shaft structure with the torsion measuring function is realized.
In this specification, the terms "a", "an", "the", "said" and "at least one" are used to indicate the presence of one or more elements/components/etc.; the terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc.; the terms "first," "second," and "third," etc. are used merely as labels, and are not limiting on the number of their objects.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A compact turbine shaft structure with torque measurement function is characterized by comprising:
the device comprises a power turbine shaft (1), wherein one end of the power turbine shaft (1) is a power input end (101), the other end of the power turbine shaft is a power output end (102), and a thin shaft (103) is arranged between the power input end (101) and the power output end (102);
the reinforcing ribs (104) are uniformly arranged on the outer peripheral wall of the thin shaft (103), the reinforcing ribs (104) extend along the axial direction of the thin shaft (103) and are arranged at intervals along the circumferential direction of the thin shaft (103), and the number of the reinforcing ribs (104) is selected as a prime number;
one end of the reference shaft (2) is suitable for being assembled on the power input end (101), the other end of the reference shaft is suitable for being assembled on the power output end (102), the axial length of the reference shaft (2) is smaller than that of the power turbine shaft (1) but larger than that of the thin shaft (103), and the reference shaft (2) is sleeved on the power turbine shaft (1);
a torque measuring ring (3), wherein the torque measuring ring (3) is suitable for being assembled on the power output end (102) and is matched with the reference shaft (2) for use to measure torque.
2. The compact turbine shaft structure with the torque measuring function of claim 1, wherein a collar (105) is arranged at one end, close to the thin shaft (103), of the power input end (101), and the power input end (101) is uniformly provided with first pin holes (107) between the collar (105) and the thin shaft (103); one end of the power output end (102) close to the thin shaft (103) is provided with a shaft shoulder (106), and second pin holes (108) are uniformly formed in the shaft shoulder (106).
3. The compact turbine shaft structure with the torque measuring function as claimed in claim 2, wherein one end of the reference shaft (2) is attached to the vertical surface of the collar (105), and the other end of the reference shaft (2) is sleeved on the shaft shoulder (106); one end of the reference shaft (2) close to the shaft collar (105) is uniformly provided with a reference shaft pin hole (201), and the other end of the reference shaft (2) is uniformly provided with a first torque measuring tooth (202).
4. The compact turbine shaft structure with the torque measuring function of claim 3, wherein one end of the reference shaft (2) close to the collar (105) is in transition fit with the power turbine shaft (1), and the other end of the reference shaft (2) is in clearance fit with the shoulder (106).
5. The compact turbine shaft structure with the torsion measuring function as claimed in claim 4, wherein the reference shaft pin hole (201) is arranged corresponding to the first pin hole (107) and is used in cooperation with the first pin (4) for limiting the axial displacement of the reference shaft (2) on the power turbine shaft (1).
6. The compact turbine shaft structure with the torsion measuring function as claimed in claim 5, wherein the torsion measuring ring (3) is sleeved on the shaft shoulder (106), torsion measuring ring pin holes (301) are uniformly formed in the torsion measuring ring (3), and second torsion measuring teeth (302) are uniformly formed in one end of the torsion measuring ring.
7. The compact turbine shaft structure with the torsion measuring function of claim 6 is characterized in that the torsion measuring ring pin hole (301) and the second pin hole (108) are arranged correspondingly and are used together with the second pin (5) for limiting the axial displacement of the torsion measuring ring (3) on the power turbine shaft (1).
8. The compact turbine shaft structure with the torsion measuring function of claim 7, wherein the first torsion measuring tooth (202) and the second torsion measuring tooth (302) form an included angle of 90 degrees therebetween in a non-working state.
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| CN113670621A (en) * | 2021-08-13 | 2021-11-19 | 上海尚实能源科技有限公司 | Torque measuring device of turboprop engine |
| FR3126459A1 (en) * | 2021-08-31 | 2023-03-03 | Safran Aircraft Engines | Aircraft turbojet comprising a turbojet shaft and a shaft stiffener. |
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| CN111982369A (en) * | 2020-07-27 | 2020-11-24 | 中国航发湖南动力机械研究所 | Output shaft torsion measuring method |
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2021
- 2021-05-06 CN CN202110491445.4A patent/CN113153439B/en active Active
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| DE3437379A1 (en) * | 1983-10-12 | 1985-04-25 | Bently Nevada Corp., Minden, Nev. | Device for measuring the rotary or bending force exerted on a shaft |
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| CN201679847U (en) * | 2010-04-13 | 2010-12-22 | 中国航空动力机械研究所 | Hollow slender flexible power output shaft |
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| CN111982369A (en) * | 2020-07-27 | 2020-11-24 | 中国航发湖南动力机械研究所 | Output shaft torsion measuring method |
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