CN214146013U

CN214146013U - High-pressure compressor rotor and vortex reducing device

Info

Publication number: CN214146013U
Application number: CN202120131939.7U
Authority: CN
Inventors: 陆晓锋; 张雯棋; 秦文
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-01-18
Filing date: 2021-01-18
Publication date: 2021-09-07
Anticipated expiration: 2031-01-18

Abstract

The high-pressure compressor rotor and the vortex reducing device have an active pressurization function so as to increase air entraining amount and reduce pressure loss. The vortex reducing device for achieving the purpose comprises a support ring and a plurality of vortex reducing pipes, wherein the vortex reducing pipes are installed on the support ring and are arranged in a divergent mode, each vortex reducing pipe is provided with a pipe center line, each pipe center line is arranged to form an included angle relative to the radial direction of the support ring, and the pipe center lines are arranged eccentrically relative to the center of the support ring.

Description

High-pressure compressor rotor and vortex reducing device

Technical Field

The utility model relates to a vortex reducing device in aeroengine's air conditioning gas circuit.

Background

With the continuous development of the aircraft engine technology, the working environment and the pressure of high-temperature components are increased, and in order to ensure the reliability and the service life of the components, novel efficient materials and efficient cooling technology are continuously applied. The efficient cooling technology mainly comprises the steps of leading out high-pressure cooling gas from a certain stage of the gas compressor to carry out cooling and sealing work on related components, and the problems of pressure drop and temperature rise along the way need to be considered in the gas leading process, so that the design of an efficient gas leading flow path becomes more important. The design goals of the bleed air flow path are therefore primarily to reduce the pressure loss of the bleed air process, to ensure the feed pressure of the cooling gas to the high-temperature components and to ensure the sealing pressure.

In the prior art, an advanced aero-engine adopts a mode of forming a hole between stages of a compressor to achieve air entraining from the radial direction to the axial direction, but in the radial air entraining process, as gas flows from a high radius to a low radius, free vortex develops violently, the generated pressure loss is large, and the development of vortex can be effectively weakened through the form of installing a vortex reducing device, so that the pressure loss in the radial internal flow process is reduced. In the existing related bleed air flow path design, some flow paths are arranged from the outside of an engine casing, and some flow paths are arranged from a central shaft cavity of an engine.

The existing high-pressure compressor rotor comprises two rotor discs and a vortex reducing device arranged in a cavity between the two rotor discs, wherein a plurality of air introducing holes are formed in the two rotor discs along the circumferential direction, and the axial direction of the air introducing holes extends along the radial direction of the rotor discs. The vortex reducing device comprises a support ring and a plurality of vortex reducing pipes, wherein the vortex reducing pipes are arranged on the support ring in a divergent mode. Since the bleed air centre line is generally in the radial direction of the vortex reducing device, the air inlet angle is not necessarily optimal and also a certain bleed air quantity is reduced and pressure losses are caused. A vortex reducing device is then required which can increase the bleed air quantity and reduce the pressure loss.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a vortex reducing device, it has initiative pressure boost function to increase bleed air volume, reduce loss of pressure.

It is a further object of the present invention to provide a high pressure compressor rotor, including the aforementioned vortex reducing device, with improved aerodynamic efficiency.

The vortex reducing device for achieving the purpose comprises a support ring and a plurality of vortex reducing pipes, wherein the vortex reducing pipes are installed on the support ring and are arranged in a divergent mode, each vortex reducing pipe is provided with a pipe center line, each pipe center line is arranged to form an included angle relative to the radial direction of the support ring, and the pipe center lines are arranged eccentrically relative to the center of the support ring.

In one embodiment, the end surface of each of the vortex reducing tubes remote from the support ring is inclined relative to the tube centre line.

In one embodiment, an end surface of each of the vortex reducing pipes, which is away from the support ring, is a slope.

In one embodiment, the vortex reducing tube is a straight tube.

In an embodiment, a plurality of said vortex reducing tubes are evenly distributed over said support ring.

The high-pressure compressor rotor comprises two rotor disks and a vortex reducing device arranged in a cavity between the two rotor disks, wherein a plurality of air holes are formed in the two rotor disks along the circumferential direction, the axial direction of each air hole extends along the radial direction of the rotor disks, and the vortex reducing device is any one of the vortex reducing devices.

The vortex reducing device has the following beneficial effects:

the vortex reducing pipe is installed in a non-radial mode, the airflow enters the vortex reducing pipe through the airflow, a certain intersection angle is formed between the airflow center and the channel center, the pipe body acts on the airflow to enable the velocity component of the airflow in the direction of the pipe body to be increased, the active pressurization effect is achieved, the air entraining quantity of the vortex reducing device is increased and the pressure loss in the air entraining process can be guaranteed in the air entraining process of the vortex reducing device, the supply and sealing pressure is provided for high-temperature parts, and enough cooling gas is provided.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a side view of a vortex reducing device;

FIG. 2 is a cross-sectional view of the vortex reducing apparatus shown in FIG. 1 taken along line C-C;

FIG. 3 is a schematic view of a bleed air flow velocity analysis of a prior art radially mounted vortex reducing apparatus;

FIG. 4 is a schematic view of an analysis of bleed air flow velocity of the non-radially mounted vortex reducing apparatus according to FIG. 1;

FIG. 5 is a schematic view of a vortex reducing tube of the vortex reducing apparatus;

FIG. 6 is a schematic view of the mounting location of the vortex reducing device within the high pressure compressor rotor.

Detailed Description

Fig. 1 and 2 show a vortex reducing device 8 for a high-pressure compressor rotor 7 of an aircraft engine, comprising a support ring 4 and a plurality of vortex reducing tubes 2, the vortex reducing tubes 2 being mounted on the support ring 4 and arranged in a diverging manner and eccentrically with respect to the support ring 4. The advantageous effect of the eccentric arrangement will be explained later in connection with fig. 3 and 4.

With reference to fig. 6, the high-pressure compressor rotor 7 comprises two

rotor disks

5, 6 and a vortex reducing device 8 mounted in the cavity between the two

rotor disks

5, 6. A plurality of bleed holes 1 are circumferentially provided in the two

rotor disks

5, 6, and the axial direction of the bleed holes 1 extends in the radial direction of the

rotor disks

5, 6. The vortex reducing device 8 is mounted in a cavity between the

rotor disks

5 and 6, and the two

rotor disks

5 and 6 and the vortex reducing device 8 rotate along the rotation axis indicated by the dashed solid line in fig. 6 and in the direction of the arrow shown in fig. 6. The air flow is sucked into the vortex reducing device 8 from the bleed air holes 1 and flows into the hub through the vortex reducing pipe 2 through the holes 9. As shown in fig. 1 and 2, the vortex reduction device 8 further includes a gland nut 3. The compression nut 3 is used for compressing the vortex reducing device 8 on the rotor disc 5, and the installation reliability of the vortex reducing device 8 is guaranteed.

As shown in fig. 1 and 2, in one embodiment of the vortex reducing device 8, the number of vortex reducing tubes 2 is 12 and is evenly distributed on the support ring 4. The vortex reducing pipe 2 is a straight pipe, so that the installation is simple and convenient, the air flow is simple in a flow path in the vortex reducing channel, and unnecessary energy loss is avoided. Furthermore, each of the vortex reducing tubes 2 has a tube centre line, which is arranged with an angle θ relative to the radial direction of the support ring 4, and is arranged eccentrically relative to the centre of the support ring 4, i.e. the tube centre line is not aligned with the centre of the support ring 4.

The vortex reducing device 8 of the present invention is further explained by comparing fig. 3 and fig. 4. Fig. 3 shows a first case in which the vortex reducing pipe 2 is radially mounted on the support ring 4, as in the case of the known vortex reducing device 8. Fig. 4 is a second case of non-radial installation of the vortex reducing pipe 2 on the support ring 4, the same as the vortex reducing device 8 of the present invention. Wherein the vortex reducing pipes 2 in fig. 3 and 4 have the same pipe diameter length L, and the distances R from the rotation axis of the vortex reducing device 8 to the other end surface 22 of the vortex reducing pipe are the same.

In the first case, as shown in fig. 3, when an air flow having a velocity V0 and an angle α with the horizontal direction of the vortex reducing pipe 2 passes through the vortex reducing pipe 2 installed in the radial direction, the air flow is acted on by the body of the vortex reducing pipe 2 to form a velocity component V1 along the pipe center line of the vortex reducing pipe 2 and a vertical component V2. Since the pipe centre line is arranged in the radial direction of the vortex reducing device 8, a certain amount of bleed air is reduced and a pressure loss is caused.

In the second case, as shown in fig. 4, similarly, when an air flow having a velocity V0 and an angle α with the horizontal direction passes through the vortex reducing pipe 2 installed in a non-radial direction, the air flow is acted on by the body of the vortex reducing pipe 2 to form a velocity component V4 along the pipe center line of the vortex reducing pipe 2 and a vertical component V3. Wherein the velocity component V4 is greater than the velocity component V1 and the vertical component V3 is less than the vertical component V2. With the non-radially mounted vortex reduction tube 2, the velocity component V4 of the air flow flowing into the center of the vortex reduction tube 2 is increased and the vertical component V3 perpendicular to the vortex reduction tube 2 is reduced due to the tube body action. Therefore, the loss caused when the airflow flows into the vortex reducing pipe 2 is reduced, the pipe body of the vortex reducing pipe 2 and the airflow act to achieve an active pressurization effect, more airflow can be introduced to flow in, and the air entraining amount is increased.

In one embodiment of the vortex reducing device 8, as shown in fig. 5, the end face 21 of the vortex reducing tube 2 remote from the support ring 4 is inclined with respect to the tube centre line, the inclined end face 21 having a larger nozzle area than the end face a of the vortex reducing tube 2 which is designed as a plane, thus increasing the flow area of the nozzle gas flow. The end surface 21 may be inclined in a manner including, but not limited to, a slope, for example, a step surface, or other opening forms that increase the area of the nozzle. When the end surface 21 of the vortex reducing pipe 2 far away from the support ring 4 is a bevel, the technical effect obtained by the method is that the design form of the end surface 21 of the vortex reducing pipe 2 is a bevel opening form, so that the processing is convenient, the flow area of the airflow at the pipe opening is increased, and the air entraining amount is further increased.

The vortex reducing device 8 is an active supercharging novel vortex reducing device, is applied to compression of an aero-engine, adopts the non-radial installation of the vortex reducing pipe 2, and the end face 21 of the vortex reducing pipe 2 is designed into an oblique opening form. In the vortex reducing pipe 2 is entered through the airflow, a certain included angle is formed between the center of the airflow and the center of the channel, the pipe body acts on the airflow to increase the velocity component V4 of the airflow along the direction of the pipe body, the active pressurization effect is achieved, and the end face 21 in the form of the inclined opening increases the flow area of the airflow. The vortex reduction device 8 can thus increase the bleed air quantity and reduce the pressure loss during the bleed air process, provide a supply and sealing pressure for high-temperature components and provide sufficient cooling gas during the bleed air process of the vortex reduction device 8.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims

1. The vortex reducing device comprises a support ring and a plurality of vortex reducing pipes, wherein the vortex reducing pipes are arranged on the support ring in a divergent mode, and the vortex reducing device is characterized in that each vortex reducing pipe is provided with a pipe center line, each pipe center line is arranged to form an included angle relative to the radial direction of the support ring, and the pipe center line is eccentrically arranged relative to the center of the support ring.

2. The vortex reducing apparatus of claim 1 wherein the end surface of each said vortex reducing tube distal to said support ring is inclined relative to said tube centerline.

3. The vortex reducing apparatus of claim 2, wherein an end surface of each of said vortex reducing tubes distal from said support ring is beveled.

4. The vortex reducing apparatus of claim 1, wherein the vortex reducing tube is a straight tube.

5. The vortex reducing apparatus of claim 1, wherein a plurality of said vortex reducing tubes are evenly distributed on said support ring.

6. A high-pressure compressor rotor comprising two rotor disks and a vortex reducing device mounted in a cavity between the two rotor disks, wherein a plurality of air holes are circumferentially arranged on the two rotor disks, and the axial direction of the air holes extends along the radial direction of the rotor disks, and the vortex reducing device is as claimed in any one of claims 1 to 5.