阅读说明：本技术 一种航空涡轮起动机离心叶轮组件及其装配方法 (Centrifugal impeller assembly of aviation turbine starter and assembly method of centrifugal impeller assembly ) 是由 武威 李文凯 刘浩 陈少俊 于 2020-07-02 设计创作，主要内容包括：本发明涉及一种航空涡轮起动机离心叶轮组件及其装配方法,该航空涡轮起动机离心叶轮组件包括叶轮,叶轮的两端平行且同轴心设置进气边、排气边,进气边与排气边之间设置轴孔,进气边与排气边之间设置多个主叶片,相邻的主叶片之间设置分流叶片,分流叶片的尾缘切角设置,即分流叶片尾端的直角部切除,以使分流叶片的出气端形成倾斜延伸面,切角结构能改变叶轮的振动频率,避免工作时其它零件对离心叶轮组件的激振。(The invention relates to an aviation turbine starter centrifugal impeller component and an assembling method thereof, the aviation turbine starter centrifugal impeller component comprises an impeller, two ends of the impeller are parallel and coaxially provided with an air inlet edge and an air outlet edge, an axle hole is arranged between the air inlet edge and the air outlet edge, a plurality of main blades are arranged between the air inlet edge and the air outlet edge, a splitter blade is arranged between adjacent main blades, and the trailing edge of the splitter blade is arranged in a corner cut mode, namely the right-angle part of the tail end of the splitter blade is cut off, so that the air outlet end of the splitter blade forms an inclined extending surface, the corner cut structure can change the vibration frequency of the impeller, and the excitation of other parts to the centrifugal impeller component during working is avoided.)

1. The utility model provides an aviation turbo starter centrifugal impeller subassembly, its characterized in that, includes the impeller, and the both ends of impeller are parallel and set up air inlet edge, exhaust edge with the axle center, set up the shaft hole between air inlet edge and the exhaust edge, set up a plurality of main blades between air inlet edge and the exhaust edge, set up splitter blade between the adjacent main blade, splitter blade's trailing edge corner cut sets up, and the right angle portion excision of splitter blade tail end promptly to make splitter blade's the end of giving vent to anger form slope extension face.

2. The aircraft turbine starter centrifugal impeller assembly according to claim 1, wherein the angle of tangency is 30 ° to 45 °, i.e. the angle between the inclined extension plane and the radial direction of the exhaust edge is 45 ° to 60 °.

3. The aircraft turbine starter centrifugal impeller assembly according to claim 1 or 2, further comprising a bushing and a nut, wherein the bushing is in interference fit with the shaft hole, the front end of the bushing is provided with a shaft thread in threaded fit with the nut, and the edge of the front end of the shaft hole on the air inlet side is provided with a sinking platform matched with the nut, so that the front end of the bushing is in threaded connection with the shaft thread through the nut after extending into the shaft hole.

4. The aircraft turbine starter centrifugal impeller assembly of claim 3, further comprising a pin, wherein the nut and the counter sink are provided with a plurality of pin holes adapted to the pin, and the nut and the air inlet edge are positioned and connected by the pin after the nut is in threaded connection with the bushing.

5. The aircraft turbine starter centrifugal impeller assembly according to claim 4, wherein a plurality of comb teeth are arranged on the outer wall of the tail end of the bushing, an internal spline is arranged on the inner wall of the tail end of the bushing, and an annular boss is arranged on the periphery of the tail end of the shaft hole.

6. The aircraft turbine starter centrifugal impeller assembly according to claim 5, further comprising a connecting pin, wherein a positioning pin hole matched with the connecting pin is formed in the periphery of the tail end of the shaft hole, and a jack matched with the connecting pin is formed in the tail end of the bushing, so that after the bushing is in threaded connection with the nut, the tail end of the bushing is in positioning connection with the exhaust edge through the connecting pin.

7. The method of assembling an aircraft turbine starter centrifugal impeller assembly according to claim 6, comprising the steps of:

A. processing an impeller, a pin, a bushing, a nut and a connecting pin according to the size requirement, wherein the bushing is matched with the shaft hole in an interference manner of 0.07-0.107 mm, the pin is matched with the pin hole in an interference manner of 0.008-0.032 mm, and the connecting pin is matched with the positioning pin hole and the jack in an interference manner of 0.008-0.032 mm;

B. heating the impeller to a temperature not lower than 160 ℃, preserving heat for not less than 30 minutes, cooling the lining to a temperature not higher than-70 ℃, and preserving heat for not less than 60 minutes; heating and cooling are carried out on the assembly fixture, then the bushing is pressed into a shaft hole of the impeller, air cooling is carried out to normal temperature, and the fixture is loosened;

C. screwing the nut at the front end of the bushing by using a torque wrench, installing the pin into the pin hole, installing the connecting pin into the positioning pin hole and the jack, positioning the bushing and the impeller, and ensuring that the end face of the nut is flush with the end face of the air inlet edge;

D. and the assembled centrifugal impeller assembly is subjected to dynamic balance, and the grinding wheel can be used for grinding the annular boss during dynamic balance until the dynamic balance meets the requirements.

8. The method for assembling an aircraft turbine starter centrifugal impeller assembly according to claim 7, wherein in the step C, the pin and the connecting pin are processed by a binding process after being assembled.

Technical Field

The invention relates to the technical field of optimization of an aviation turbine starter centrifugal impeller assembly, in particular to an aviation turbine starter centrifugal impeller assembly and an assembling method thereof.

Background

From the birth of aviation gas turbine starters to the rapid development of the starters nowadays, the vibration problem occurs in almost all the starter development and use processes. The centrifugal impeller assembly is one of the important rotor components in the starter, and its own vibration problem must be taken into sufficient consideration. In the prior art, the centrifugal impeller assembly of the aviation turbine starter is structurally shown in fig. 1 and comprises a gas inlet edge 14 and a gas outlet edge 15 which are arranged in parallel and coaxially, a shaft hole 10 is arranged between the gas inlet edge 14 and the gas outlet edge 15, a plurality of streamline main blades 11 are arranged between the gas inlet edge 14 and the gas outlet edge 15, and splitter blades 12 are arranged between adjacent main blades 11, as shown in fig. 2, wherein a right-angled part 16 is arranged at the gas outlet end of each splitter blade 12, namely, a right-angled part 16 which is approximate to a right angle is formed between an outer meridian plane 17 and an axial extension plane 18 of each splitter blade. Therefore, optimizing the centrifugal impeller assembly structure, reducing vibration, and improving reliability of parts are important development directions of the gas turbine starter.

Disclosure of Invention

The invention aims to provide an aviation turbine starter centrifugal impeller assembly which is simple in structure and avoids vibration and an assembling method thereof.

In order to solve the technical problem, the centrifugal impeller assembly of the aviation turbine starter comprises an impeller, wherein two ends of the impeller are parallel and are coaxially provided with an air inlet edge and an air outlet edge, an axle hole is formed between the air inlet edge and the air outlet edge, a plurality of main blades are arranged between the air inlet edge and the air outlet edge, a splitter blade is arranged between adjacent main blades, and the tail edge of the splitter blade is arranged in a corner cut mode, namely the right-angled part of the tail end of the splitter blade is cut off, so that the air outlet end of the splitter blade forms an inclined extension surface, and the corner cut structure can change the vibration frequency of the impeller and avoid the excitation of other parts to the centrifugal impeller assembly during working.

Further, the angle of the tangent angle is 30-45 degrees, namely the included angle between the inclined extension surface and the radial direction of the exhaust edge is 45-60 degrees.

Furthermore, aviation turbine starter centrifugal impeller subassembly still includes bush and nut, bush and shaft hole interference fit, the front end of bush set up with nut screw-thread fit's axle thread, arrange the edge setting of the front end in the shaft hole on the air inlet edge with the heavy platform of nut looks adaptation to carry out threaded connection by nut and axle thread after making the front end of bush stretch into the shaft hole.

Furthermore, the centrifugal impeller component of the aviation turbine starter further comprises a pin, a plurality of pin holes matched with the pin are formed in the nut and the sinking platform, and the nut and the air inlet edge are positioned and connected through the pin after the nut is in threaded connection with the bushing.

Further, the outer wall of the tail end of the lining is provided with a plurality of comb teeth, the inner wall of the tail end of the lining is provided with an internal spline, and the periphery of the tail end of the shaft hole is provided with an annular boss.

Furthermore, the centrifugal impeller assembly of the aviation turbine starter further comprises a connecting pin, a positioning pin hole matched with the connecting pin is formed in the periphery of the tail end of the shaft hole, and a jack matched with the connecting pin is formed in the tail end of the bushing, so that after the bushing is in threaded connection with the nut, the tail end of the bushing is in positioning connection with the exhaust edge through the connecting pin.

The assembling method of the centrifugal impeller assembly of the aviation turbine starter comprises the following steps:

A. the impeller, the pin, the bushing, the nut and the connecting pin are processed according to the size requirement, wherein the bushing is matched with the shaft hole in an interference mode of 0.07-0.107 mm, the pin is matched with the pin hole in an interference mode of 0.008-0.032 mm, and the connecting pin is matched with the positioning pin hole and the jack in an interference mode of 0.008-0.032 mm.

B. Heating the impeller to a temperature not lower than 160 ℃, preserving heat for not less than 30 minutes, cooling the lining to a temperature not higher than-70 ℃, and preserving heat for not less than 60 minutes; heating and cooling are carried out on the assembly fixture, then the bush is pressed into the shaft hole of the impeller, air cooling is carried out to normal temperature, and the fixture is loosened.

C. And screwing the nut at the front end of the bushing by using a torque wrench, installing the pin into the pin hole, installing the connecting pin into the positioning pin hole and the jack, positioning the bushing and the impeller, and ensuring that the end face of the nut is flush with the end face of the air inlet edge.

D. And the assembled centrifugal impeller assembly is subjected to dynamic balance, and the grinding wheel can be used for grinding the annular boss during dynamic balance until the dynamic balance meets the requirements.

Further, in the step C, the pin and the connecting pin are assembled and then processed by adopting a binding process, so that the pin and the connecting pin are prevented from falling off.

The invention has the technical effects that: (1) compared with the prior art, the centrifugal impeller assembly of the aviation turbine starter has the advantages that the trailing edge of the splitter blade of the centrifugal impeller assembly is subjected to the optimized structure design of the cutting angle, so that the excitation caused by the centrifugal impeller assembly and a related structure during working can be avoided, the vibration frequency of the centrifugal impeller assembly is changed, the resonance rotating speed is effectively changed, the reliability of the centrifugal impeller assembly is improved, and the service life of the centrifugal impeller assembly is prolonged; (2) the nut is connected with the bushing through threads, the nut is fixed through the pin, radial play is reduced, interference is guaranteed between the impeller and the bushing, meanwhile, the impeller and the bushing are fixed through the two connecting pins on the rear end face of the impeller, and the problem that the interference requirement between the impeller and the bushing cannot be met due to deformation of the inner diameter of the impeller in working is solved; (3) the arrangement of the annular boss can ensure that the assembled centrifugal impeller assembly passes a dynamic balance test; (4) the bushing and the shaft hole, the pin and the pin hole are in interference fit, hot charging and cold charging are combined, the bushing and the shaft hole, the pin and the pin hole can be conveniently assembled, and the assembling precision is ensured.

Drawings

The invention is described in further detail below with reference to the drawings of the specification:

FIG. 1 is a schematic perspective view of a prior art centrifugal impeller assembly of an aircraft turbine starter;

FIG. 2 is an enlarged partial schematic view of area A of FIG. 1;

FIG. 3 is an axial structural schematic view of an aircraft turbine starter centrifugal impeller assembly of the present invention;

FIG. 4 is a schematic view of another angle configuration of the aircraft turbine starter centrifugal impeller assembly of the present invention;

FIG. 5 is a schematic view, partially in section, of the centrifugal impeller assembly of the aircraft turbine starter of the present invention;

FIG. 6 is a schematic perspective view of an aircraft turbine starter centrifugal impeller assembly according to the present invention;

FIG. 7 is an enlarged fragmentary schematic view of the trailing edge of the splitter blade of the aircraft turbine starter centrifugal impeller assembly of the present invention.

In the figure: the impeller comprises an impeller 1, a shaft hole 10, a main blade 11, a splitter blade 12, an annular boss 13, an air inlet edge 14, an air exhaust edge 15, a right-angled part 16, an outer meridian plane 17, an axial extension plane 18, an inclined extension plane 19, a liner 2, a labyrinth 21, an internal spline 22, a shaft thread 23, a nut 3, a pin 4 and a connecting pin 5.

Detailed Description