CN114526322A - Birotor aeroengine accessory transmission system - Google Patents

Abstract

The present application provides a dual-rotor aero-engine accessory transmission system, including: a central transmission case, which has a high-pressure rotor and a low-pressure rotor, and the high-pressure rotor and the low-pressure rotor connect the high-pressure rotor and the low-pressure central bevel gear through the high-pressure stage central bevel gear and the low-pressure stage central bevel gear. The transmission axis of the power and speed of the low pressure rotor is transformed; the high pressure stage transmission rod and the low pressure stage transmission rod are respectively connected to the high pressure stage central bevel gear and the low pressure stage central bevel gear, so as to transmit the power and motion of the high pressure rotor and the low pressure rotor to the an accessory transmission case; and an accessory transmission case, in which the power and rotational speed transmission axes of the high pressure stage transmission rod and the low pressure stage transmission rod are converted again through the high pressure stage central bevel gear and the low pressure stage central bevel gear, wherein, There are multiple accessories in the accessory transmission case, and the multiple accessories are distributed into two groups, the high pressure stage transmission rod drives the first accessory group through the spur gear pair, and the low pressure stage transmission rod drives the second accessory group through the spur gear pair.

Description

A dual-rotor aero-engine accessory transmission system

technical field

The present application belongs to the technical field of aero-engines, and in particular relates to a double-rotor aero-engine accessory transmission system.

Background technique

Power extraction refers to the power required by the aero-engine accessory drive system to extract the accessory from the main shaft. It is the most important indicator for evaluating the accessory drive system. The size of the power extraction directly determines the ability of the driven accessories, which in turn affects the engine performance.

For a dual-rotor aero-engine, the power extraction of the accessory drive system mainly comes from the high-pressure rotor or low-pressure rotor of the engine, and the power is transmitted to the outside of the engine through the central drive case, which is provided with an accessory drive case outside the engine. The gear shaft is arranged in the middle to match the speed and drive the accessories. At the same time, the speed of the engine rotor can be measured by the speed sensor using the gear in the accessory transmission case.

A typical method for extracting power and rotational speed of an accessory drive system is shown in Figure 1. In a typical accessory drive system 10, there is an engine rotor 12 in the central drive case 11, and a plurality of accessories and rotational speed sensors 19 in the accessory drive case 13— That is, the first accessory 15 , the second accessory 16 , the third accessory 17 , and the fourth accessory 18 , the accessory transmission case 13 is arranged on the outer side of the central transmission case 11 , and the power is extracted through the transmission shaft 13 and distributed to each accessory.

The existing technical solution extracts power from a single engine rotor, and is a single transmission chain, which is limited by the strength of a single pair of gears in the transmission chain that carry the full power, and the extraction power is limited, which cannot meet the increasing power extraction requirements of accessories; in addition, In this method, only a single engine rotor speed can be extracted from the accessory transmission case, and the speed of the engine rotor can be directly measured. The sensor needs to be inserted from the outside of the engine to the vicinity of the rotor, which has a large span and is difficult to arrange.

SUMMARY OF THE INVENTION

The purpose of the present application is to provide a dual-rotor aero-engine accessory transmission system to solve or alleviate at least one problem in the background art.

The technical solution of the present application is: a dual-rotor aero-engine accessory transmission system, characterized in that the system includes:

The central transmission case has a high pressure rotor and a low pressure rotor, and the high pressure rotor and the low pressure rotor transmit the power and rotational speed of the high pressure rotor and the low pressure rotor through the high pressure stage central bevel gear and the low pressure stage central bevel gear The axis is transformed;

The high pressure stage transmission rod and the low pressure stage transmission rod for transmitting power and rotation speed, the high pressure stage transmission rod and the low pressure stage transmission rod are respectively connected to the high pressure stage central bevel gear and the low pressure stage central bevel gear, thereby connecting the high pressure rotor and the low pressure rotor. transmission of power and motion to the accessory drive case; and

An accessory transmission casing, in which the power and rotational speed transmission axes of the high pressure stage transmission rod and the low pressure stage transmission rod are converted again through the high pressure stage central bevel gear and the low pressure stage central bevel gear, wherein the accessory transmission There are multiple accessories in the casing, and the multiple accessories are distributed into two groups, the high pressure stage transmission rod drives the first accessory group through the spur gear pair, and the low pressure stage transmission rod drives the second accessory group through the spur gear pair.

Further, the high pressure stage transmission rod and the low pressure stage transmission rod are coaxially arranged.

Further, the high pressure stage transmission rod and the low pressure stage transmission rod are not coaxially arranged.

Further, the first accessory group and the second accessory group are distributed in relative positions in the accessory transmission casing.

Further, a high-pressure rotational speed sensor is provided in the one-side accessory transmission casing of the first accessory group, and the high-pressure rotational speed sensor measures the rotational speed of the gear and obtains the rotational speed of the high-pressure rotor by converting the gear ratio.

Further, a low-pressure rotational speed sensor is provided in the one-side accessory transmission casing of the second accessory group, and the low-pressure rotational speed sensor measures the rotational speed of the gear and obtains the rotational speed of the low-pressure rotor by converting the gear ratio.

The dual-rotor aero-engine accessory drive system provided in this application can extract power and rotational speed from both the high and low pressures of the engine, avoid the limitation of the strength of a single drive sprocket, increase the total power that the accessory drive system can extract, and improve the drive capability of the accessory, thereby Improve engine performance, and at the same time can measure the speed of the two rotors of the engine in the accessory transmission system, which is convenient for the arrangement of the speed sensor.

Description of drawings

In order to more clearly illustrate the technical solutions provided by the present application, the accompanying drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application.

FIG. 1 is a schematic diagram of a typical accessory drive system in the prior art.

FIG. 2 is a schematic diagram of an accessory transmission system according to an embodiment of the application.

FIG. 3 is a schematic diagram of an accessory transmission system according to another embodiment of the present application.

Reference number:

10 - Typical accessory drivetrain

11-Central drive case

12-Engine rotor

13- Transmission rod

14-Accessory drive case

15-Appendix 1

16-Annex II

16-Annex III

18-Annex IV

19-speed sensor

20-coaxial accessory drivetrain

21-Central drive receiver

221-High pressure rotor

222-High pressure stage central bevel gear

231-Low pressure rotor

232-Low pressure stage central bevel gear

24-Accessory Transmission Receiver

251-Annex I

252-Annex II

253-Annex III

254-Annex IV

261-High pressure speed sensor

262-Low Pressure Speed Sensor

271-High pressure stage center bevel gear

272-Low pressure stage center bevel gear

281-High pressure stage transmission rod

282-Low pressure stage transmission rod

30- Different shaft attachment drive system

31-Central drive receiver

321-High pressure rotor

322-High pressure stage central bevel gear

331-Low pressure rotor

332-Low pressure stage central bevel gear

34-Accessory drive case

351-Annex I

352-Annex II

353-Appendix III

354-Annex IV

361-High Pressure Speed Sensor

362-Low Pressure Speed Sensor

371-High pressure stage center bevel gear

372-Low pressure stage center bevel gear

381-High pressure stage transmission rod

382-Low pressure stage transmission rod

Detailed ways

In order to make the implementation purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.

The present application proposes a dual-rotor aero-engine accessory transmission system. The accessory transmission system extracts power and rotational speed from the high and low-voltage rotors of the engine at the same time, and at the same time, there are two transmission chains that can be used to drive the accessories, which improves the capability of the accessory transmission system. The total power extracted can meet higher accessory requirements. The speed of the two rotors of the engine is simultaneously measured through the accessory transmission case. The arrangement of the speed sensor is simple and convenient.

FIG. 2 shows a twin-rotor aero-engine accessory drive system according to an embodiment of the application. The twin-rotor aero-engine accessory drive system in this embodiment is a coaxial accessory drive system 20 . Specifically, the coaxial accessory drive system 20 includes a central drive casing 21 and an accessory drive casing 24, and the central drive casing 21 has a high-pressure rotor 221 and a low-pressure rotor 231, and the high-pressure rotor 221 and the low-pressure rotor 231 pass through the high-pressure stage The central bevel gear 222 and the low-pressure-stage central bevel gear 232 change the transmission axis of the power and the rotational speed of the high-pressure rotor 221 and the low-pressure rotor 231 to the vertical direction, and the high-pressure stage transmission rod 281 and the low-pressure stage transmission rod 282 are coaxially arranged and connected to each other. The high pressure stage central bevel gear 222 and the low pressure stage central bevel gear 232 transmit the power and motion/rotation speed of the high pressure rotor 221 and the low pressure rotor 231 to the accessory transmission case 24 . The accessory transmission case 24 has a plurality of accessories, and in this embodiment, there are four accessories, namely the first accessory 251 , the second accessory 251 , the third accessory 253 and the fourth accessory 254 . The accessories are roughly distributed into two groups, namely, the first accessory 251 and the second accessory 251 are distributed on the right side of the accessory transmission case 24 , and the third accessory 253 and the fourth accessory 254 are distributed on the left side of the accessory transmission case 24 . In the accessory transmission case 24, the high-pressure-stage central bevel gear 271 and the low-pressure-stage central bevel gear 272 again convert the power and rotational speed transmission axes of the high-pressure-stage transmission rod 281 and the low-pressure-stage transmission rod 282 to horizontal in this embodiment . The high pressure stage transmission rod 281 drives the right attachment 1 251 and the second attachment 252 through the spur gear pair, and the low pressure stage transmission rod 282 drives the left attachment 3 253 and the attachment 4 254 through the spur gear pair. Finally, a high pressure rotational speed sensor 261 and a low pressure rotational speed sensor 262 are respectively provided on the left and right sides of the accessory transmission casing 24 , the gear rotational speed is measured by the high pressure rotational speed sensor 261 , the rotational speed of the high pressure rotor 221 is obtained by converting the transmission ratio, and the low pressure rotational speed sensor 262 measures the rotational speed of the gear. The rotational speed of the gear is converted into the rotational speed of the low pressure rotor 231 by the gear ratio.

It should be noted that the accessory drive system described in this embodiment is a coaxial arrangement of the high and low rotor drive chains, but the functions implemented in this application are not limited by the position of the gear axis, and can be arranged separately, and the accessory drive system drives You can have any number of attachments.

FIG. 3 shows a twin-rotor aero-engine accessory drive system according to another embodiment of the application. The twin-rotor aero-engine accessory drive system in this embodiment is an off-axis accessory drive system 30 . Specifically, the coaxial accessory drive system 30 includes a central drive casing 31 and an accessory drive casing 34, and the central drive casing 31 has a high-pressure rotor 321 and a low-pressure rotor 331, and the high-pressure rotor 321 and the low-pressure rotor 331 pass through the high-pressure stage The central bevel gear 322 and the low-pressure stage central bevel gear 332 change the transmission axis of the power and rotational speed of the high-pressure rotor 321 and the low-pressure rotor 331 to the vertical direction, and the high-pressure stage transmission rod 381 and the low-pressure stage transmission rod 382 are arranged non-coaxially and connected respectively. To the high pressure stage central bevel gear 322 and the low pressure stage central bevel gear 332 , thereby transmitting the power and motion/speed of the high pressure rotor 321 and the low pressure rotor 331 to the accessory drive case 34 . The accessory transmission case 34 has a plurality of accessories, and in this embodiment, there are also four accessories, namely the first accessory 351 , the second accessory 351 , the third accessory 353 and the fourth accessory 354 . The accessories are roughly distributed into two groups, namely, the first accessory 351 and the second accessory 351 are distributed on the right side of the accessory transmission case 34 , and the third accessory 353 and the fourth accessory 354 are distributed on the left side of the accessory transmission case 34 . In the accessory transmission case 34, the high-pressure-stage central bevel gear 371 and the low-pressure-stage central bevel gear 372 again convert the power and rotational speed transmission axes of the high-pressure-stage transmission rod 281 and the low-pressure-stage transmission rod 282, which in this embodiment are converted to horizontal . The high pressure stage transmission rod 381 drives the right attachment 351 and the second attachment 352 through the spur gear pair, and the low pressure stage transmission rod 382 drives the left attachment 353 and the attachment IV 354 through the spur gear pair. Finally, a high pressure rotational speed sensor 361 and a low pressure rotational speed sensor 362 are respectively provided on the left and right sides of the accessory transmission casing 34 , the gear rotational speed is measured by the high pressure rotational speed sensor 361 , and the rotational speed of the high pressure rotor 321 is obtained by converting the transmission ratio, which is measured by the low pressure rotational speed sensor 362 The rotational speed of the gear is converted into the rotational speed of the low pressure rotor 331 by the gear ratio.

The dual-rotor aero-engine accessory drive system provided in this application can extract power and rotational speed from both the high and low pressures of the engine, avoid the limitation of the strength of a single drive sprocket, increase the total power that the accessory drive system can extract, and improve the drive capability of the accessory, thereby Improve engine performance, and at the same time can measure the speed of the two rotors of the engine in the accessory transmission system, which is convenient for the arrangement of the speed sensor.

The above are only specific embodiments of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed in the present application, All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims (6)

1. A dual-rotor aero-engine accessory transmission system, characterized in that the system comprises: The central transmission case has a high pressure rotor and a low pressure rotor, and the high pressure rotor and the low pressure rotor transmit the power and rotational speed of the high pressure rotor and the low pressure rotor through the high pressure stage central bevel gear and the low pressure stage central bevel gear The axis is transformed; The high pressure stage transmission rod and the low pressure stage transmission rod for transmitting power and rotation speed, the high pressure stage transmission rod and the low pressure stage transmission rod are respectively connected to the high pressure stage central bevel gear and the low pressure stage central bevel gear, thereby connecting the high pressure rotor and the low pressure rotor. transmission of power and motion to the accessory drive case; and An accessory transmission casing, in which the power and rotational speed transmission axes of the high pressure stage transmission rod and the low pressure stage transmission rod are converted again through the high pressure stage central bevel gear and the low pressure stage central bevel gear, wherein the accessory transmission There are multiple accessories in the casing, and the multiple accessories are distributed into two groups, the high pressure stage transmission rod drives the first accessory group through the spur gear pair, and the low pressure stage transmission rod drives the second accessory group through the spur gear pair. 2 . The dual-rotor aero-engine accessory transmission system according to claim 1 , wherein the high pressure stage transmission rod and the low pressure stage transmission rod are coaxially arranged. 3 . 3. The dual-rotor aero-engine accessory transmission system according to claim 1, wherein the high-pressure stage transmission rod and the low-pressure stage transmission rod are arranged non-coaxially. 4. The dual-rotor aero-engine accessory drive system according to claim 2 or 3, wherein the first accessory group and the second accessory group are distributed in opposite positions in the accessory drive case. 5. The dual-rotor aero-engine accessory transmission system according to claim 4, wherein a high-pressure rotational speed sensor is provided in the one-side accessory transmission casing of the first accessory group, and the high-pressure rotational speed sensor measures the gear rotational speed and passes the The transmission ratio is converted to obtain the rotational speed of the high-pressure rotor. 6. The dual-rotor aero-engine accessory transmission system according to claim 4, wherein a low-pressure rotational speed sensor is provided in the one-side accessory transmission casing of the second accessory group, and the low-pressure rotational speed sensor measures the gear rotational speed and passes the The transmission ratio is converted to obtain the rotational speed of the low pressure rotor.

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