CN212553676U

CN212553676U - Gas turbine high pressure rotor rocking system and tool

Info

Publication number: CN212553676U
Application number: CN202021284610.6U
Authority: CN
Inventors: 季寅泽; 刘震宇; 范骏鹏
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-07-03
Filing date: 2020-07-03
Publication date: 2021-02-19
Anticipated expiration: 2030-07-03

Abstract

The utility model provides a gas turbine high pressure rotor system, instrument of cranking, it is not through switching gear box, annex gear box and the high pressure rotor after the assembly of direct drive low pressure system is accomplished. To achieve the stated object, a gas turbine high pressure rotor cranking tool wherein the drive link has an inner end and an outer end; the mounting cylinder is provided with two bearing mounting portions spaced apart in the axial direction; the two bearings are respectively arranged on the two bearing mounting parts; the rotating mandrel is rotatably supported by the two bearings; the mounting bracket is used for being fixed on the intermediate casing and supporting the mounting cylinder; the inner end of the transmission rod is in splined connection with a radial input shaft of a central transmission gear box at the front end of the high-pressure rotor, and the outer end of the transmission rod is in splined connection with the inner end of the rotating mandrel.

Description

Gas turbine high pressure rotor rocking system and tool

Technical Field

The invention relates to a gas turbine high-pressure rotor rocking mechanism.

Background

In the assembly process of the aircraft engine, the high-pressure rotor is often required to be rotated to check whether the rotation is flexible or not, or the high-pressure rotor is fixed at a certain angle, so that assembly and test work can be conveniently carried out.

At present, the international advanced aircraft engine with a large bypass ratio generally adopts a double-rotor or even three-rotor design to obtain better working performance, because a high-pressure rotor is distributed at the core part of the engine, a low-pressure system penetrates through a high-pressure rotor shaft, a low-pressure compressor at the front end of the low-pressure system and a low-pressure turbine at the rear end of the low-pressure system seal the core inside, and an operator cannot directly rotate the high-pressure rotor after the low-pressure system is assembled. The current common technology is to transmit the torque to the high-pressure rotor for rotation in the form of driving the accessory gearbox after the assembly of the adapter gearbox and the accessory gearbox is completed, and the scheme mainly has the following defects:

1. a time difference exists between the low-pressure system assembling and the adapting gear box and the accessory gear box assembling, and the high-pressure rotor cannot rotate in the time difference.

2. The transmission gears and accessories of the switching gear box and the accessory gear box are numerous, the torque transmission is lost, and the rotating torque of the high-pressure rotor cannot be measured independently.

3. During the development of the engine, if the clamping stagnation is detected after the assembly of the adapter gearbox and the accessory gearbox is completed, the fault reason cannot be quickly positioned.

4. The high-pressure rotor cannot be fixed.

Therefore, there is a need for a tool solution that directly drives the high pressure rotor without using the adaptor gearbox and the accessory gearbox to compensate for the above disadvantages.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a gas turbine high pressure rotor instrument of cranking, it is not through switching gear box, annex gear box and the high pressure rotor after the assembly of direct drive low pressure system is accomplished.

Another object of the present invention is to provide a gas turbine high pressure rotor cranking system, comprising the above tool.

To achieve the stated object, a gas turbine high pressure rotor cranking tool wherein the drive link has an inner end and an outer end; the mounting cylinder is provided with two bearing mounting portions spaced apart in the axial direction; the two bearings are respectively arranged on the two bearing mounting parts; the rotating mandrel is rotatably supported by the two bearings; the mounting bracket is used for being fixed on the intermediate casing and supporting the mounting cylinder; the inner end of the transmission rod is in splined connection with a radial input shaft of a central transmission gear box at the front end of the high-pressure rotor, and the outer end of the transmission rod is in splined connection with the inner end of the rotating mandrel.

In one or more embodiments, the mounting bracket provides a stop receptacle, the rotating mandrel has a stop hole, and the stop receptacle is aligned with the stop hole;

the gas turbine high-pressure rotor cranking tool further comprises a stop bolt, and the stop bolt can be inserted into the stop jack and the stop hole in a pluggable mode.

In one or more embodiments, the gas turbine high pressure rotor cranking tool further comprises a crank connected to an outer end of the rotating mandrel.

In one or more embodiments, the outer end of the rotating mandrel has a swing square head, and the crank has a square hole and is sleeved on the swing square head.

In one or more embodiments, the mounting cylinder has an inner end and an outer end, the inner bore of the inner end of the mounting cylinder has an inner shoulder, the inner bore of the outer end of the mounting cylinder has an outer shoulder, and one of the bearings is mounted in the inner bore of the inner end of the mounting cylinder, abuts against the inner shoulder, and is pressed by a first pressing plate fixed to the inner end of the mounting cylinder; and the other bearing is arranged in an inner hole at the outer end of the mounting cylinder, abuts against the outer shaft shoulder and is pressed by a second pressing plate fixed at the outer end of the mounting cylinder.

In one or more embodiments, the mounting bracket includes a mounting plate, the mounting plate is provided with mounting plate holes, the mounting cylinder with the mounting plate hole cooperation, the outer end of mounting cylinder still has a mounting cylinder flange, the mounting cylinder flange with mounting plate bolted connection.

In one or more embodiments, the mounting bracket has a hanging ring welded thereto.

The gas turbine high-pressure rotor rocking system for achieving the purpose comprises a central transmission gear box installed at the front end of a high-pressure rotor, wherein the central transmission gear box comprises a radial input shaft, the radial input shaft is provided with a spline, and the gas turbine high-pressure rotor rocking system further comprises a gas turbine high-pressure rotor rocking tool.

The utility model has the advantages that:

1. the high-pressure rotor can be directly driven without depending on the transfer gearbox and the accessory gearbox to transmit rotating torque, and when the high-pressure rotor is shaken, the high-pressure rotor is not limited by the assembly of a low-pressure system, the transfer gearbox and the accessory gearbox.

2. The method is favorable for accurately measuring the rotating torque of the high-pressure rotor.

3. If the high-pressure system is blocked, whether the fault occurs at the high-pressure rotor or in the switching gear box or the accessory gear box can be quickly judged.

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 partial schematic view of a gas turbine high pressure rotor cranking tool installation.

FIG. 2 is a perspective view of a gas turbine high pressure rotor cranking tool.

FIG. 3 is a schematic diagram of the combination of a gas turbine high pressure rotor cranking tool.

Fig. 4 is a schematic view of the transmission rod.

FIG. 5 is a perspective view of a gas turbine high pressure rotor cranking tool without a drive shaft.

Fig. 6 is a cross-sectional view of the portion shown in fig. 5.

Fig. 7 is a perspective view of the rotating mandrel.

FIG. 8 is a schematic view of the dead bolt installation.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

As shown in FIG. 7, the rotating mandrel 26 has a third spline 261 at the inner end and a teeter square 262 at the outer end.

As shown in fig. 1 and 2, the gas turbine high pressure rotor cranking tool 2 is mounted on the intermediate casing 3, passes through the mounting hole of the intermediate casing 3, and is connected with a fourth spline 70 of an input shaft of the central transmission gear box 7 mounted on the front end of the high pressure rotor. The above and the following interior and exterior are referred to with the gas turbine high-pressure rotor turning tool attached to an intermediate casing of a gas turbine.

As shown in fig. 5 and 6, the rotating shaft 26 is mounted on two bearings, i.e., the first bearing 22 and the second bearing 24, and is rotatably supported by the two bearings. The first bearing 22 is mounted on a bearing mounting portion at the inner end of the mounting tube 21, and the second bearing 24 is mounted on a bearing mounting portion at the outer end of the mounting tube 21.

The mounting bracket includes a mounting plate 30, as shown in fig. 1, the mounting plate 30 is square, has four legs, and corresponds to the four elevating members 5 fixed on the intermediate casing 3, and the four legs are connected to the four elevating members 5 by fasteners 28, respectively, thereby lifting the mounting plate 30 by a height.

Returning to fig. 5 and 6, the mounting plate 30 has a mounting plate hole 300, and the mounting cylinder 21 is mounted in the mounting hole 300, whereby the mounting bracket is supported by the intermediate casing 3, the mounting cylinder 21 is supported by the mounting bracket, and the rotating spindle 26 is supported by the mounting cylinder 21.

As shown in fig. 1 to 3, the gas turbine high pressure rotor cranking tool further includes a transmission rod 1, and the transmission rod 1 has a first spline 11 at an inner end and a second spline 12 at an outer end. The first spline 11 and the fourth spline 70 are in splined connection, one of which is an internal spline and the other is an external spline. The second spline 12 is splined to the third spline 261, and likewise, one of the splines is an internal spline and the other spline is an external spline. After the transmission rod 1 is connected with the rotating mandrel 26, the high-pressure rotor can be rotated by rotating the rotating mandrel 26, so that the high-pressure rotor is not limited by the assembly of a low-pressure system, a switching gearbox and an accessory gearbox. By means of the connection of the rotating mandrel 26 and the torque wrench, the rotating torque of the high-pressure rotor can be accurately measured without introducing the rotating torque transmission loss of the transfer gearbox and the accessory gearbox. If the high-pressure system is blocked, the fault can be quickly judged to occur at the high-pressure rotor. If the adapter gear box and the accessory gear box are stuck after being installed, the fault can be judged to be generated in the adapter gear box and the accessory gear box.

As shown in fig. 8, the mounting bracket further includes a vertical plate 31, a stop insertion hole 211 is disposed on the vertical plate 31, accordingly, the rotating mandrel 26 has a stop hole 263, and the stop insertion hole 211 is aligned with the stop hole 263. The locking latch 29 is insertably inserted into the locking insertion hole 211 and the locking hole 263 so that the rotating spindle 26 is locked to rotate, thereby locking the high-pressure rotor.

As shown in fig. 5, a crank 27 is connected to the outer end of the rotation shaft 26, and the shaft 26 is rotated by the crank 27 with less effort. The handle 27 has a square hole and fits over the rotating mandrel 26 counter to the square head 262 to allow for torque transfer and easy removal.

As shown in fig. 6, the inner bore 211 of the inner end of the mounting cylinder 21 has an inner shoulder 212, the inner bore 219 of the outer end of the mounting cylinder 21 has an outer shoulder 218, and the first bearing 22 is mounted in the inner bore 211 of the inner end of the mounting cylinder, abuts against the inner shoulder 212, and is pressed by the first pressing plate 23 fixed to the inner end of the mounting cylinder 21. The second bearing 24 is mounted in an inner bore 219 at the outer end of the mounting cylinder 21 and abuts against the outer shoulder 218 and is pressed by a second pressing plate 25 fixed to the outer end of the mounting cylinder 21. The two bearings are thereby mounted and fixed by a compact structure, providing rotatable support to the rotating spindle 26.

The fixing of the mounting plate 30 to the mounting cylinder 21 is achieved in a manner similar to a flange connection. As shown in fig. 6, the mounting plate 30 is provided with mounting plate holes 300, the mounting cylinder 21 is matched with the mounting plate holes 300, the outer end of the mounting cylinder 21 is further provided with a mounting cylinder flange 215, and the mounting cylinder flange 215 is bolted to the mounting plate 30. This structure realizes positioning of the mounting cylinder 21 and fastening connection by bolts.

As shown in fig. 5, a hanging ring 31 is welded to the mounting bracket. The entire swing tool can be transported and moved by means of the lifting ring 31.

As shown in fig. 1, after the gas turbine high-pressure rotor cranking tool is mounted on the intermediate casing 3, the gas turbine high-pressure rotor cranking tool and the central transmission gear box mounted at the front end of the high-pressure rotor constitute a gas turbine high-pressure rotor cranking system, and the gas turbine high-pressure rotor cranking system is not limited by the assembly of a low-pressure system, the assembly of a transfer gear box and an accessory gear box, so that the gas turbine high-pressure rotor cranking system has various beneficial effects.

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. Gas turbine high pressure rotor rocking tool, its characterized in that includes:

a drive link having an inner end and an outer end;

a mounting cylinder provided with two bearing mounts spaced apart in an axial direction;

two bearings respectively mounted on the two bearing mounting parts;

the rotating mandrel is rotatably supported by the two bearings; and

the mounting bracket is used for being fixed on the intermediate casing and supporting the mounting cylinder;

the inner end of the transmission rod is in splined connection with a radial input shaft of a central transmission gear box at the front end of the high-pressure rotor, and the outer end of the transmission rod is in splined connection with the inner end of the rotating mandrel.

2. The gas turbine high pressure rotor cranking tool as defined in claim 1 wherein said mounting bracket provides a stop receptacle, said rotating mandrel having a stop hole, said stop receptacle aligned with said stop hole;

3. The gas turbine high pressure rotor cranking tool as recited in claim 2, further comprising a crank handle connected to an outer end of said turning spindle.

4. The gas turbine high pressure rotor tool of claim 3, wherein said rotating mandrel has a square head at its outer end, and said crank has a square hole and fits over said square head.

5. The gas turbine high pressure rotor cranking tool as defined in claim 1 wherein said mounting cylinder has an inner end and an outer end, said mounting cylinder inner bore having an inner shoulder and said mounting cylinder outer bore having an outer shoulder, one of said bearings being mounted in said mounting cylinder inner bore and abutting said inner shoulder and being compressed by a first compression plate secured to said mounting cylinder inner end; and the other bearing is arranged in an inner hole at the outer end of the mounting cylinder, abuts against the outer shaft shoulder and is pressed by a second pressing plate fixed at the outer end of the mounting cylinder.

6. The gas turbine high pressure rotor cranking tool as defined in claim 1, wherein said mounting bracket includes a mounting plate provided with mounting plate holes, said mounting cylinder engaging said mounting plate holes, said mounting cylinder further having a mounting cylinder flange at an outer end thereof, said mounting cylinder flange being bolted to said mounting plate.

7. The gas turbine high pressure rotor cranking tool as defined in claim 1 wherein a hoisting ring is welded to said mounting bracket.

8. A gas turbine high pressure rotor cranking system comprising:

a central drive gearbox mounted at the front end of the high pressure rotor, the central drive gearbox including a radial input shaft, the radial input shaft having splines,

it is characterized in that the preparation method is characterized in that,

the gas turbine high pressure rotor cranking tool of any one of claims 1 to 7 is further included.