CN111535867A - Power turbine short shaft, turboshaft engine and aircraft - Google Patents
Power turbine short shaft, turboshaft engine and aircraft Download PDFInfo
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- CN111535867A CN111535867A CN202010380739.5A CN202010380739A CN111535867A CN 111535867 A CN111535867 A CN 111535867A CN 202010380739 A CN202010380739 A CN 202010380739A CN 111535867 A CN111535867 A CN 111535867A
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- 230000000994 depressogenic effect Effects 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 6
- 238000013461 design Methods 0.000 description 13
- 230000000694 effects Effects 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 230000002265 prevention Effects 0.000 description 4
- 238000007792 addition Methods 0.000 description 2
- 238000012217 deletion Methods 0.000 description 2
- 230000037430 deletion Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000010485 coping Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
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Classifications
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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
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
- F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
- F16B35/06—Specially-shaped heads
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B39/00—Locking of screws, bolts or nuts
- F16B39/22—Locking of screws, bolts or nuts in which the locking takes place during screwing down or tightening
- F16B39/24—Locking of screws, bolts or nuts in which the locking takes place during screwing down or tightening by means of washers, spring washers, or resilient plates that lock against the object
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B39/00—Locking of screws, bolts or nuts
- F16B39/22—Locking of screws, bolts or nuts in which the locking takes place during screwing down or tightening
- F16B39/24—Locking of screws, bolts or nuts in which the locking takes place during screwing down or tightening by means of washers, spring washers, or resilient plates that lock against the object
- F16B39/26—Locking of screws, bolts or nuts in which the locking takes place during screwing down or tightening by means of washers, spring washers, or resilient plates that lock against the object with spring washers fastened to the nut or bolt-head
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B41/00—Measures against loss of bolts, nuts, or pins; Measures against unauthorised operation of bolts, nuts or pins
- F16B41/002—Measures against loss of bolts, nuts or pins
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Abstract
The invention provides a power turbine short shaft, a turboshaft engine and an aircraft. The power turbine short shaft comprises a shaft body, a turbine disc, a plurality of tension bolts and a retainer ring. The turbine disk encircles and sets up in the axis body and has flange, and a plurality of axial through bolt holes have been seted up to flange's periphery, and the part that is located between per two adjacent bolt holes of the preceding terminal surface of turbine disk is provided with the fender circle groove respectively, and the notch in fender circle groove is along radially inwards seting up. The plurality of tension bolts respectively and detachably penetrate through the plurality of bolt holes, and the screw heads of the tension bolts are stopped at front end orifices of the bolt holes. The retainer ring is arranged around the shaft body and is detachably clamped in the retainer ring grooves, and the part of the retainer ring which is not clamped in the retainer ring grooves is pressed against the screw head of the tension bolt. The anti-rotation and anti-falling functions of the tension bolt can be quickly realized by utilizing the check ring, the assembly performance is better, the quick installation can be realized without hot assembly and auxiliary assembly tools, and the arc-shaped end teeth of the power turbine unit body are not influenced.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a power turbine short shaft and turboshaft engine and an aircraft.
Background
The existing turboshaft engine usually adopts a unit body structure, for example, the unit body is divided into a core machine unit body, an output shaft unit body and a power turbine unit body, and the design of the unit body structure can realize the quick replacement and installation of the power turbine unit body of the outfield engine and improve the maintenance grade of the engine.
Fig. 1 representatively illustrates a perspective view of a power turbine stub shaft of an existing turboshaft engine, and fig. 2 representatively illustrates a structural schematic view of a tension bolt of the power turbine stub shaft of the existing turboshaft engine. As shown in fig. 1 and 2, the power turbine stub shaft 101 plays a role in transmitting torque between the power turbine unit and an output shaft in the aeroengine, and the power turbine stub shaft 101 and the power turbine unit are connected by a tension bolt 102.
In the assembly process of the existing turboshaft engine adopting the unit body structure, firstly, the power turbine short shaft 101 is connected with the output shaft unit body, the power turbine short shaft 101 can be connected with the power turbine unit body through the arc end teeth, and at the moment, the head of the tension bolt 102 is arranged at the disk center of the turbine disk, and no space is available for fixing the tension bolt 102, so that anti-falling and anti-rotation measures must be taken for the tension bolt 102 in advance. It is common to prevent the tie bolts 102 from falling out by interference fitting the tie bolts 102 with the bolt holes of the power turbine stub shaft 101.
However, the tightening bolts 102 and the bolt holes are in interference fit, and although the bolts can be prevented from falling off to a certain extent, larger interference is not suitable, because the larger interference can cause deformation of the arc-shaped end teeth, influence is caused on the centering and torque transmission of the arc-shaped end teeth, and even serious problems can cause overlarge vibration of the power turbine rotor and the like. Moreover, the above-mentioned existing scheme is also not suitable for using the smaller interference magnitude to realize the anti-drop function of the tension bolt 102, because the smaller interference magnitude can make the tension bolt 102 still have the possibility of dropping, possibly dropping into the engine, causing the engine to decompose, reducing the assembly efficiency.
Disclosure of Invention
It is a primary object of the present invention to overcome at least one of the above-mentioned drawbacks of the prior art and to provide a power turbine stub shaft that does not require hot assembly, achieves a better assembly effect, and has no effect on the circular arc end teeth.
Another main object of the present invention is to overcome at least one of the drawbacks of the prior art described above and to provide a turboshaft engine having a power turbine stub shaft as described above.
It is a further primary object of the present invention to overcome at least one of the above-mentioned drawbacks of the prior art and to provide an aircraft having a turboshaft engine as described above.
In order to achieve the purpose, the invention adopts the following technical scheme:
according to one aspect of the invention, a power turbine stub shaft is provided. The power turbine short shaft comprises a shaft body, a turbine disc, a plurality of tension bolts and a retainer ring. The turbine disc is arranged around the shaft body and is provided with a connecting flange, a plurality of bolt holes which axially penetrate through the connecting flange are formed in the periphery of the connecting flange, retaining ring grooves are respectively formed in the parts, located between every two adjacent bolt holes, of the front end face of the turbine disc, and notches of the retaining ring grooves are formed inwards in the radial direction. The plurality of tensioning bolts respectively and detachably penetrate through the plurality of bolt holes, and the screw heads of the tensioning bolts are stopped at front end orifices of the bolt holes. The retainer ring is arranged around the shaft body and is detachably clamped in the retainer ring grooves, and the part of the retainer ring which is not clamped in the retainer ring grooves is pressed against the screw heads of the tensioning bolts.
According to one embodiment of the invention, the periphery of the turbine disk is circumferentially provided with a plurality of convex parts and a plurality of concave parts, and the convex parts and the concave parts are alternately distributed; wherein, a plurality of bolt holes are located respectively a plurality of depressed parts, a plurality of fender circle grooves are located respectively a plurality of bellying.
According to one embodiment of the invention, the periphery of the screw head has two opposite flat surfaces. When the tension bolt penetrates through the bolt hole, the two planes of the screw head are respectively limited in the two adjacent protruding parts at two sides, so that the rotation of the tension bolt is prevented.
According to one embodiment of the present invention, the plurality of bolt holes are uniformly distributed in the circumferential direction of the turbine disk, and the plurality of retainer grooves are uniformly distributed in the circumferential direction of the turbine disk.
According to one embodiment of the invention, the rear end of the connecting flange is provided with circular arc end teeth; and the number of the bolt holes is the common divisor of the tooth number of the arc end tooth.
According to one embodiment of the invention, the shank of the tensioning bolt is a clearance fit with the bolt hole.
According to one embodiment of the invention, the tolerance band of the clearance fit relationship between the screw and the bolt hole is H7/g 6.
According to one embodiment of the invention, the collar is a circlip or a helical collar.
According to another aspect of the invention, a turboshaft engine is provided, comprising a power turbine stub shaft and a power turbine unit body. Wherein the power turbine stub shaft is the power turbine stub shaft proposed by the present invention and described in the above embodiments, and the power turbine stub shaft is connected to the power turbine unit body by the plurality of tie bolts.
According to yet another aspect of the invention, an aircraft is provided that includes an aircraft engine. Wherein the aircraft engine is a turboshaft engine as set forth in the present invention and described in the above embodiments.
According to the technical scheme, the advantages and positive effects of the power turbine short shaft, the turboshaft engine and the aircraft are as follows:
the invention provides a power turbine short shaft which comprises a shaft body, a turbine disc, a plurality of tension bolts and a retainer ring. The turbine disk encircles and sets up in the axis body, and a plurality of axial through's bolt hole has been seted up to the periphery of turbine disk, and the part that is located between per two adjacent bolt holes of the preceding terminal surface of turbine disk is provided with the fender circle groove respectively, and the notch in fender circle groove is along radially inwards seting up. The plurality of tension bolts respectively and detachably penetrate through the plurality of bolt holes, and the screw heads of the tension bolts are stopped at front end orifices of the bolt holes. The retainer ring is arranged around the shaft body and is detachably clamped in the retainer ring grooves, and the part of the retainer ring which is not clamped in the retainer ring grooves is pressed against the screw head of the tension bolt. Through the design, the power turbine short shaft provided by the invention can utilize the check ring to quickly realize the functions of rotation prevention and falling prevention of the tension bolt, has better assembly performance, does not need the hot assembly of the tension bolt and the bolt hole in interference fit in the existing scheme, can realize quick installation without an auxiliary assembly tool, and has no influence on the arc end teeth of the power turbine unit body.
Drawings
Various objects, features and advantages of the present invention will become more apparent from the following detailed description of preferred embodiments of the invention, when considered in conjunction with the accompanying drawings. The drawings are merely exemplary of the invention and are not necessarily drawn to scale. In the drawings, like reference characters designate the same or similar parts throughout the different views. Wherein:
FIG. 1 is a perspective view of a power turbine stub shaft of a prior art turboshaft engine;
FIG. 2 is a schematic structural view of the tension bolt of the power turbine stub shaft illustrated;
FIG. 3 is a perspective view of a power turbine stub shaft shown in accordance with an exemplary embodiment;
FIG. 4 is a side view of the power turbine stub shaft shown in FIG. 3;
FIG. 5 is a cross-sectional view taken along line A-A of FIG. 4;
FIG. 6 is a cross-sectional view taken along line B-B of FIG. 4;
FIG. 7 is an enlarged view of portion C of FIG. 6;
FIG. 8 is a schematic structural view of a tension bolt of the power turbine stub shaft shown in FIG. 3;
FIG. 9 is a left side view of FIG. 8;
FIG. 10 is a schematic illustration of a portion of a turboshaft engine shown in accordance with an exemplary embodiment.
The reference numerals are explained below:
101. a power turbine stub shaft;
102. tightening the bolts;
200. a power turbine stub shaft;
210. a shaft body;
220. a turbine disk;
221. bolt holes;
222. a retainer groove;
223. a boss portion;
224. a recessed portion;
225. circular arc end teeth;
230. tightening the bolts;
231. a screw head;
2311. a plane;
232. a screw;
240. a retainer ring;
300. a power turbine unit body.
Detailed Description
Exemplary embodiments that embody features and advantages of the invention are described in detail below. It is to be understood that the invention is capable of other and different embodiments and its several details are capable of modification without departing from the scope of the invention, and that the description and drawings are accordingly to be regarded as illustrative in nature and not as restrictive.
In the following description of various exemplary embodiments of the invention, reference is made to the accompanying drawings, which form a part hereof, and in which are shown by way of illustration various exemplary structures, systems, and steps in which aspects of the invention may be practiced. It is to be understood that other specific arrangements of parts, structures, example devices, systems, and steps may be utilized and structural and functional modifications may be made without departing from the scope of the present invention. Moreover, although the terms "over," "between," "within," and the like may be used in this specification to describe various example features and elements of the invention, these terms are used herein for convenience only, e.g., in accordance with the orientation of the examples described in the figures. Nothing in this specification should be construed as requiring a specific three dimensional orientation of structures in order to fall within the scope of the invention.
Referring to fig. 3, a perspective view of a power turbine stub shaft as proposed by the present invention is representatively illustrated. In the exemplary embodiment, the power turbine stub shaft proposed by the present invention is explained by taking the application to a turboshaft engine as an example. Those skilled in the art will readily appreciate that various modifications, additions, substitutions, deletions, or other changes may be made to the specific embodiments described below in order to utilize the concepts of the present invention in connection with other types of aircraft engines or other equipment, and such changes are within the scope of the principles of the power turbine short shaft as set forth herein.
As shown in fig. 3, in the present embodiment, the power turbine stub shaft 200 according to the present invention mainly includes a shaft body 210, a turbine disc 220, a plurality of tie bolts 230, and a retainer ring 240. Referring additionally to FIGS. 4-9, a side view of the power turbine stub shaft 200 is representatively illustrated in FIG. 4; FIG. 5 representatively illustrates a cross-sectional view taken along line A-A of FIG. 4; representatively illustrated in fig. 6 is a cross-sectional view taken along line B-B of fig. 4; fig. 7 representatively illustrates an enlarged view of portion C of fig. 6; representatively illustrated in FIG. 8 is a schematic structural view of the tension bolt 230 of the power turbine stub shaft 200; the left side view of fig. 8 is representatively illustrated in fig. 9. The structure, connection mode and functional relationship of the main components of the power turbine stub shaft 200 according to the present invention will be described in detail below with reference to the drawings.
As shown in fig. 3 to 7, in the present embodiment, the turbine disk 220 is disposed around the shaft body 210, for example, at the rear end of the shaft body 210 (i.e., the end connected to the power turbine unit body 300). The rear end of the turbine disk 220 has a connecting flange, and a plurality of bolt holes 221 are formed in the periphery of the connecting flange so as to axially penetrate therethrough. The parts of the front end surface of the turbine disk 220, which are located between every two adjacent bolt holes 221, are respectively provided with a retainer groove 222, and the notch of the retainer groove 222 opens inward in the radial direction. The rear end of the turbine disk 220 is also provided with circular arc end teeth 225 in the circumferential direction. The tension bolts 230 are detachably inserted into the bolt holes 221, and the heads 231 of the tension bolts 230 are stopped at the front end holes of the bolt holes 221. The retainer 240 is disposed around the shaft body 210, and the retainer 240 is removably engaged in the plurality of retainer grooves 222, and a portion of the retainer 240 that is not engaged in the retainer grooves 222 is pressed against the head 231 of the tightening bolt 230. In other words, the retaining ring grooves 222 may be an integral annular groove structure, and the integral groove structure is separated by the bolt holes 221 formed in the connecting flange, so that the circumferentially discontinuous groove structure, i.e., the retaining ring grooves 222, is formed. Through the design, the power turbine short shaft 200 provided by the invention can rapidly realize the anti-rotation and anti-falling functions of the tension bolt 230 by using the retainer ring 240, has good assembly performance, does not need the hot assembly of the tension bolt 230 and the bolt hole 221 which are in interference fit in the existing scheme, can be rapidly installed without an auxiliary assembly tool, and has no influence on the arc-shaped end tooth 225 of the power turbine unit body 300.
Preferably, as shown in fig. 3 to 7, in the present embodiment, the periphery of the turbine disk 220 may be preferably formed with a plurality of convex portions 223 and a plurality of concave portions 224 along the circumferential direction, and the convex portions 223 and the concave portions 224 are alternately distributed, that is, one concave portion 224 is respectively provided on both sides of each convex portion 223 along the circumferential direction of the turbine disk 220, and one convex portion 223 is respectively provided on both sides of each concave portion 224 along the circumferential direction of the turbine disk 220. On this basis, the plurality of bolt holes 221 may be preferably located in the plurality of recesses 224, for example, at the bottoms of the recesses 224, respectively, and the plurality of retainer grooves 222 may be preferably located on the plurality of protrusions 223, for example, on the inner side surfaces of the protrusions 223 facing the shaft body 210, respectively.
In addition, as shown in fig. 3 to 7, based on the design of the convex portions 223 and the concave portions 224 of the turbine disk 220, in the present embodiment, the concave portions 224 formed between adjacent two convex portions 223 also define a structure of a "mounting groove" that receives and positions the screw head 231 of the tie bolt 230, facilitating the installation and positioning of the bolt.
Further, as shown in fig. 8 and 9, based on the design in which one convex portion 223 is provided on each of both sides of each concave portion 224, in the present embodiment, the outer circumference of the head 231 of the tightening bolt 230 may preferably have two opposite flat surfaces 2311. Accordingly, when the tightening bolt 230 is inserted into the bolt hole 221 in the recess 224, the two flat surfaces 2311 of the screw head 231 can be respectively restrained by the two adjacent convex portions 223 on both sides. With the above-described design, the tightening bolt 230 can be prevented from rotating in the bolt hole 221. In addition, the cross section of the screw head 231 in the radial direction of the turbine disk 220 may be a general circle, and the screw head 231 may be machined with the flat surfaces 2311 on both sides, so as to realize the structure of the screw head 231 described in the present embodiment. In other embodiments, the cross section of the screw head 231 in the radial direction of the turbine disc 220 may also be preferably substantially a double flush circle (i.e., a figure enclosed by two parallel opposite chord sides of equal length and two arcs arranged oppositely and having equal corresponding central angles), a rectangle or other polygon, and the number of sides of the polygon may be preferably an even number.
Preferably, as shown in fig. 3 to 7, in the present embodiment, the plurality of bolt holes 221 may be preferably uniformly distributed in the circumferential direction of the turbine disk 220. Also, the plurality of retainer grooves 222 may preferably be uniformly distributed in the circumferential direction of the turbine disk 220.
Preferably, as shown in fig. 4, in the present embodiment, 10 bolt holes 221 may be preferably formed on the turbine disc 220. In other embodiments, the number of the bolt holes 221 formed in the turbine disc 220 can be flexibly adjusted according to the connection requirement between the power turbine stub shaft 200 and the power turbine unit 300, for example, 6, 8, 9, 12, etc., but is not limited to this embodiment.
Further, as shown in fig. 4, based on the design that the plurality of bolt holes 221 are uniformly distributed in the circumferential direction of the turbine disc 220, and based on the design that 10 bolt holes 221 are opened in the turbine disc 220, in the present embodiment, on the plane 2311 (i.e., the radial plane 2311) where the turbine disc 220 is located, the hole centers of each bolt hole 221 are symmetrically connected along the axis circumference of the shaft body 210, and the included angle between adjacent bolt holes 221 is 36 ° (the included angle between 10 uniformly distributed bolt holes 221 is shown in fig. 4). In other embodiments, the number of the bolt holes 221 may be selected according to the number of teeth of the circular-arc end tooth 225, and the number of the bolt holes 221 may preferably be a common divisor of the number of teeth of the circular-arc end tooth 225, so as to ensure that the bolt holes 221 all pass through between the teeth or tooth spaces of the circular-arc end tooth 225.
Preferably, in the present embodiment, the screw 232 (shown in fig. 8) of the tension bolt 230 is in clearance fit with the bolt hole 221. Accordingly, compared with the design of the interference fit between the bolt and the hole in the prior art, the design of the interference fit is improved into the clearance fit, because the retainer ring 240 can provide a sufficient anti-falling effect, and the two planes 2311 on the screw head 231 of the tension bolt 230 can further provide an anti-rotation effect, the improvement of the clearance fit between the tension bolt 230 and the bolt hole 221 can ensure that the tension bolt 230 cannot move, rotate and loosen after being tensioned axially, the installation of the tension bolt 230 can be easier and more convenient in the assembly process, a hot assembly mode is not required to be used in the installation process of the bolt for coping with the design of the interference fit, and any deformation influence on the arc-shaped end tooth 225 is not caused.
Further, based on the design of the screw 232 of the tension bolt 230 and the bolt hole 221 in a clearance fit manner, in the present embodiment, the tolerance band of the clearance fit relationship of the screw 232 and the bolt hole 221 may be preferably H7/g 6. In other embodiments, the tolerance band of the clearance fit relationship between the screw 232 and the bolt hole 221 can be selected to have other values, such as a larger tolerance band, and is not limited to this embodiment.
Preferably, in the present embodiment, the retainer ring 240 may preferably be a spiral retainer ring 240, a circlip 240, or the like. In the retainer ring 240 having the above-described structure, when the retainer ring 240 is pressed from the expanded state to the compressed state when the retainer ring 240 is pressed and held in the plurality of retainer ring grooves 222 by the biasing force applied thereto in the expanded state for mounting, the degree of firmness of mounting the retainer ring 240 and the pressing effect on the screw heads 231 of the respective tie bolts 230 can be further optimized by the change in the structural state of the retainer ring 240.
It should be noted herein that the power turbine stub shafts illustrated in the drawings and described in the present specification are but a few examples of the wide variety of power turbine stub shafts in which the principles of the present invention can be employed. It should be clearly understood that the principles of the present invention are in no way limited to any of the details of the power turbine stub shaft or any of the components of the power turbine stub shaft shown in the drawings or described in this specification.
Based on the above detailed description of the power turbine stub shaft proposed by the present invention, an exemplary embodiment of the turboshaft engine proposed by the present invention will be described below
Referring to fig. 10, there is representatively illustrated a schematic view of a portion of the structure of a turboshaft engine in accordance with the present invention. In the exemplary embodiment, the turboshaft engine proposed by the present invention is explained taking an aircraft engine applied to an aircraft as an example. Those skilled in the art will readily appreciate that many modifications, additions, substitutions, deletions, or other changes may be made to the embodiments described below in order to utilize the teachings of the present invention in other types of equipment, and still be within the scope of the principles of the turboshaft engine set forth herein.
As shown in fig. 10, in the present embodiment, the turboshaft engine proposed by the present invention includes at least a power turbine stub shaft 200 and a power turbine unit 300. Among them, the power turbine stub shaft 200 may employ the power turbine stub shaft 200 proposed by the present invention and described in detail in the above embodiments. Specifically, the power turbine stub shaft 200 is connected to the power turbine unit body 300 by a plurality of tie bolts 230.
It should be noted herein that the turboshaft engines illustrated in the drawings and described in this specification are but a few examples of the wide variety of turboshaft engines that can employ the principles of the present invention. It should be clearly understood that the principles of the present invention are in no way limited to any of the details of the turboshaft engine or any of the components of the turboshaft engine shown in the drawings or described in this specification.
Based on the above exemplary description of the power turbine stub shaft and turboshaft engine proposed by the present invention, the aircraft proposed by the present invention will be described in the following.
In this embodiment, the aircraft proposed by the invention comprises at least an aircraft engine. In which the aircraft engine may preferably employ the turboshaft engine proposed by the present invention and described in detail in the above embodiments.
It should be noted herein that the aircraft illustrated in the figures and described in this specification are only a few examples of the wide variety of aircraft that could employ the principles of the present invention. It should be clearly understood that the principles of this invention are in no way limited to any of the details of the aircraft or any of the components of the aircraft shown in the drawings or described in this specification.
In summary, the power turbine stub shaft provided by the invention comprises a shaft body, a turbine disc, a plurality of tension bolts and a retaining ring. The turbine disk encircles and sets up in the axis body, and a plurality of axial through's bolt hole has been seted up to the periphery of turbine disk, and the part that is located between per two adjacent bolt holes of the front end flange face of turbine disk, power turbine minor axis are provided with the fender circle groove respectively, and the notch in fender circle groove is seted up along radial inwards. The plurality of tension bolts respectively and detachably penetrate through the plurality of bolt holes, and the screw heads of the tension bolts are stopped at front end orifices of the bolt holes. The retainer ring is arranged around the shaft body and is detachably clamped in the retainer ring grooves, and the part of the retainer ring which is not clamped in the retainer ring grooves is pressed against the screw head of the tension bolt. Through the design, the power turbine short shaft provided by the invention can utilize the check ring to quickly realize the functions of rotation prevention and falling prevention of the tension bolt, has better assembly performance, does not need the hot assembly of the tension bolt and the bolt hole in interference fit in the existing scheme, can realize quick installation without an auxiliary assembly tool, and has no influence on the arc end teeth of the turbine short shaft.
Exemplary embodiments of a power turbine stub shaft, a turboshaft engine, and an aircraft proposed by the present invention are described and/or illustrated in detail above. Embodiments of the invention are not limited to the specific embodiments described herein, but rather, components and/or steps of each embodiment may be utilized independently and separately from other components and/or steps described herein. Each component and/or step of one embodiment can also be used in combination with other components and/or steps of other embodiments. When introducing elements/components/etc. described and/or illustrated herein, the articles "a," "an," and "the" are intended to mean that there are one or more of the 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. Furthermore, the terms "first" and "second" and the like in the claims and the description are used merely as labels, and are not numerical limitations of their objects.
While the present invention has been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.
Claims (10)
1. A power turbine stub shaft, comprising:
a shaft body;
the turbine disc is arranged around the shaft body and provided with a connecting flange, a plurality of bolt holes which axially penetrate through the turbine disc are formed in the periphery of the connecting flange, retaining ring grooves are respectively formed in the parts, located between every two adjacent bolt holes, of the front end face of the turbine disc, and notches of the retaining ring grooves are formed inwards in the radial direction;
the tensioning bolts respectively and detachably penetrate through the bolt holes, and screw heads of the tensioning bolts are stopped at front end orifices of the bolt holes; and
and the retaining ring is arranged around the shaft body and is detachably clamped in the retaining ring grooves, and the part of the retaining ring which is not clamped in the retaining ring grooves is pressed against the screw head of the tensioning bolt.
2. The power turbine stub shaft of claim 1, wherein the periphery of the turbine disk is circumferentially formed with a plurality of raised portions and a plurality of recessed portions, each raised portion and each recessed portion being alternately distributed; wherein, a plurality of bolt holes are located respectively a plurality of depressed parts, a plurality of fender circle grooves are located respectively a plurality of bellying.
3. The power turbine stub shaft of claim 2 wherein the periphery of the screw head has two opposing flats; when the tension bolt penetrates through the bolt hole, the two planes of the screw head are respectively limited in the two adjacent protruding parts at two sides, so that the rotation of the tension bolt is prevented.
4. The power turbine stub shaft of claim 1, wherein the plurality of bolt holes are evenly distributed in a circumferential direction of the turbine disk, and the plurality of retainer grooves are evenly distributed in the circumferential direction of the turbine disk.
5. The power turbine stub shaft of claim 4 wherein the attachment flange aft end is provided with radiused end teeth; and the number of the bolt holes is the common divisor of the tooth number of the arc end tooth.
6. The power turbine stub shaft of claim 1 wherein the shank of the tie bolt is a clearance fit with the bolt hole.
7. The power turbine stub shaft of claim 6 wherein the tolerance band for the clearance fit relationship of the screw and bolt hole is H7/g 6.
8. The power turbine stub shaft of claim 6, wherein the retaining ring is a circlip or a helical retaining ring.
9. A turboshaft engine comprising a power turbine stub shaft and a power turbine unit body, wherein the power turbine stub shaft is the power turbine stub shaft according to any one of claims 1 to 8, and the power turbine stub shaft is connected to the power turbine unit body through the plurality of tie bolts.
10. An aircraft comprising an aircraft engine, wherein the aircraft engine is the turboshaft engine of claim 9.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010380739.5A CN111535867B (en) | 2020-05-08 | 2020-05-08 | Power turbine short shaft, turboshaft engine and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010380739.5A CN111535867B (en) | 2020-05-08 | 2020-05-08 | Power turbine short shaft, turboshaft engine and aircraft |
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| CN111535867B CN111535867B (en) | 2022-07-08 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112360886A (en) * | 2020-10-28 | 2021-02-12 | 中国航发湖南动力机械研究所 | Disc shaft connecting structure |
| CN112417593A (en) * | 2020-11-18 | 2021-02-26 | 西北工业大学 | Optimization method for connection assembly mounting angle of circular arc end teeth of aircraft engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070110565A1 (en) * | 2005-11-16 | 2007-05-17 | General Electric Company | Methods and apparatuses for cooling gas turbine engine rotor assemblies |
| CN102069463A (en) * | 2009-11-25 | 2011-05-25 | 西门子公司 | Retainer |
| CN203476510U (en) * | 2013-08-22 | 2014-03-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Connecting structure for power turbine disc of combustion gas turbine |
| CN107269316A (en) * | 2017-08-17 | 2017-10-20 | 中南大学 | A kind of disc of conical profile structure of gas turbine central draw bar type rotor |
| CN110486093A (en) * | 2018-05-14 | 2019-11-22 | 中国航发湖南动力机械研究所 | Turbogenerator and turbine rotor connection structure |
-
2020
- 2020-05-08 CN CN202010380739.5A patent/CN111535867B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070110565A1 (en) * | 2005-11-16 | 2007-05-17 | General Electric Company | Methods and apparatuses for cooling gas turbine engine rotor assemblies |
| CN102069463A (en) * | 2009-11-25 | 2011-05-25 | 西门子公司 | Retainer |
| CN203476510U (en) * | 2013-08-22 | 2014-03-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Connecting structure for power turbine disc of combustion gas turbine |
| CN107269316A (en) * | 2017-08-17 | 2017-10-20 | 中南大学 | A kind of disc of conical profile structure of gas turbine central draw bar type rotor |
| CN110486093A (en) * | 2018-05-14 | 2019-11-22 | 中国航发湖南动力机械研究所 | Turbogenerator and turbine rotor connection structure |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112360886A (en) * | 2020-10-28 | 2021-02-12 | 中国航发湖南动力机械研究所 | Disc shaft connecting structure |
| CN112360886B (en) * | 2020-10-28 | 2022-03-25 | 中国航发湖南动力机械研究所 | Disc shaft connecting structure |
| CN112417593A (en) * | 2020-11-18 | 2021-02-26 | 西北工业大学 | Optimization method for connection assembly mounting angle of circular arc end teeth of aircraft engine |
| CN112417593B (en) * | 2020-11-18 | 2024-02-23 | 西北工业大学 | Optimization method for connection assembly installation angle of arc end teeth of aero-engine |
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| Publication number | Publication date |
|---|---|
| CN111535867B (en) | 2022-07-08 |
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