CN112012966B

CN112012966B - Balancing assembly, rotor system, gas turbine and balancing method

Info

Publication number: CN112012966B
Application number: CN201910456974.3A
Authority: CN
Inventors: 林见南; 杨凌元; 马天宇
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2019-05-29
Filing date: 2019-05-29
Publication date: 2022-05-31
Anticipated expiration: 2039-05-29
Also published as: CN112012966A

Abstract

The invention relates to a gas turbine, a rotor system, a balancing assembly for balancing the rotor system and a balancing method, wherein the balancing assembly comprises a balancing screw for connecting an air inlet cone rear supporting ring of the rotor system along the circumferential direction, the balancing screw is provided with a groove extending from a head end to a tail end of the balancing screw, the groove comprises a groove head part and a groove body part extending from the groove head part, and the groove body part is used for accommodating a first mass balancing piece.

Description

Balancing assembly, rotor system, gas turbine and balancing method

Technical Field

The invention relates in particular to a balancing assembly, a rotor system, a gas turbine and a balancing method.

Background

The axial flow aircraft engine is composed of a high-pressure rotor and a low-pressure rotor, wherein the low-pressure rotor is composed of a fan supercharging stage and a low-pressure turbine, and the high-pressure rotor is composed of a high-pressure compressor and a high-pressure turbine. In the design and manufacturing process of the aeroengine, due to the fact that materials are uneven or blank defects are caused, errors are generated in machining and assembly, even when the aeroengine is designed, the aeroengine has various factors such as asymmetric geometric shapes, and the like, centrifugal inertia forces of rotating parts cannot be counteracted with each other when the aeroengine runs normally, the centrifugal inertia forces act on other parts through bearings, vibration is caused, noise is generated, abrasion of the bearings is accelerated, the service life of the engine is shortened, and a destructive accident that a person is destroyed by a machine can be caused in serious cases. The rotor of the engine must therefore be balanced to the permitted level of balance, with the amplitude of the mechanical vibrations being within the permitted range.

Currently, the rotor needs to be balanced during the manufacturing or maintenance of the engine.

The dynamic balancing method changes the mass distribution of the rotor by removing weight or balancing weight on the rotor, thereby reducing the dynamic load on the bearing to an allowable range and achieving the aim of smooth running of the engine. At present, the balance of parts is balanced in a weight removing mode under most conditions, when the parts are assembled to form assemblies or parts for balancing, a weight balancing mode is mostly adopted, and the rotor reaches the required balance range by adjusting the weight.

The specific balancing structure usually includes balancing screws with different weights mounted at different positions of the circumference of the air inlet cone to perform balancing or balancing blocks with different sizes mounted on the fan disc to perform dynamic balancing on the fan rotor. The balance weight/balance screw for balancing weight all adopts similar structural design, through increasing or reducing the size on certain characteristic, changes the height, length or thickness of balance weight/balance screw to change its weight, this kind of method needs many times dismouting to change, sometimes can't reach required equilibrium volume, still needs to carry out on-the-spot coping to balance weight/balance screw simultaneously, influences balancing efficiency greatly.

Disclosure of Invention

It is an object of the present invention to provide a balancing assembly for balancing a rotor system of a gas turbine.

It is another object of the present invention to provide a rotor system for a gas turbine.

It is a further object of the present invention to provide a gas turbine engine.

It is a further object of the present invention to provide a balancing method for a rotor system of a gas turbine.

A balancing assembly according to one aspect of the invention for balancing a rotor system of a gas turbine comprises a balancing screw for circumferentially connecting an inlet cone rear support ring of the rotor system, the balancing screw having a recess opening from a head end thereof to a tail end thereof, the recess comprising a recess head and a recess body extending from the recess head, the recess body accommodating a first mass balancing member.

In an embodiment of the balancing assembly, the side wall of the body part of the recess comprises an internal thread structure, and the first mass balance member comprises an external screw member, which is fastened to the recess in a threaded connection with the internal thread structure.

In an embodiment of the balancing assembly, the distance of the tail end of the external screw member from the tail end of the balancing screw is more than 8 mm.

In an embodiment of the balancing assembly, the first mass balance comprises a filler, which is accommodated inside the body part of the recess.

In an embodiment of the balancing assembly, the first mass balance comprises a pin fastened to the recess by an interference fit connection with the body of the recess.

According to one aspect of the invention, the balancing component is used for balancing a rotor system of a gas turbine, and comprises a balancing block part arranged on a fan disc of the rotor system, wherein the balancing block part comprises a balancing block body and a balancing hole, the balancing block body is provided with a connecting hole and the balancing hole, the connecting hole is used for fastening a connecting piece of the balancing block body and the fan disc, and the balancing hole is used for arranging a second mass balancing piece inside the balancing hole.

In an embodiment of the balancing assembly, the second mass balance comprises a screw or a pin, the pin being in interference fit connection with the balancing hole.

A rotor system for a gas turbine engine according to another aspect of the present invention includes a balancing assembly as described in any one of the above.

A gas turbine according to yet another aspect of the present invention includes the rotor system described above.

A balancing method according to still another aspect of the present invention includes:

arranging balance screws on a rear support ring of an air inlet cone of a rotor system along the circumferential direction, arranging grooves on the balance screws, fixedly arranging first mass balance pieces in the grooves, and balancing the rotor system by adjusting the equivalent mass of the first mass balance pieces; or a fan disc of the rotor system is provided with a balance block part, the balance block part is provided with a balance hole, a second mass balance piece is fixedly arranged in the balance hole, and the rotor system is balanced by adjusting the equivalent mass of the second mass balance piece.

In an embodiment of the balancing method, the equivalent mass of the first mass balance is adjusted by one or more of the following steps: the side wall of the groove is provided with an internal thread structure, the first mass balancing piece comprises an external thread piece, the external thread piece and the internal thread structure are in threaded connection and fastened in the groove, and the equivalent mass is adjusted by adjusting the depth of the external thread piece screwed into the body part of the groove or adjusting the mass of the external thread piece; the first mass balance piece comprises a filler, the uncured filler is filled into the groove, the filler is integrated with the balance screw after being cured, and the equivalent mass is adjusted by adjusting the mass of the filled filler.

The invention has the advantages that under the condition of not changing the external structure and the size of the balance screw/balance block, the groove or the balance hole is arranged in the balance screw/balance block part with the same specification, the first mass balancing piece or the second mass balancing piece is arranged in the groove or the balance hole, the number of the balance screws/balance blocks with different specifications which need to be arranged in the design process is reduced, the complicated working procedures caused by the need of carrying out on-site grinding and adding work on the balance screw in the balance process are avoided, and the balance efficiency is effectively improved. The weight of the balance screw/balance block part is adjusted on line by filling fillers of different materials or screwing screws with different lengths, and the weight of the balance screw/balance block is adjusted in the dynamic balance process, so that the processing cost of the balance screw is reduced, and the process procedure is simplified; meanwhile, the design consistency of the balance screws/balance blocks is remarkably improved, only one type of the specification of the threaded holes of the balance screws/balance blocks is needed, the processing error rate is reduced, and the processing efficiency is improved; meanwhile, the design has the advantages of small change on the existing structure, convenient processing and cost saving.

Drawings

The above and other features, characteristics and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and examples, wherein it is to be noted that the drawings are given by way of illustration only, are not drawn to scale, and should not be taken as limiting the scope of the invention, which is actually claimed, wherein:

FIG. 1 is a partial schematic structural view of a rotor system of a gas turbine according to an embodiment.

Fig. 2 is a schematic view of a balance screw according to an embodiment.

Fig. 3 is a schematic structural view of a balance screw according to another embodiment.

Fig. 4 is a schematic structural diagram of a balancing block according to an embodiment.

Fig. 5 is a schematic structural view of a weight portion according to another embodiment.

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 joined to a second element, the description includes embodiments in which the first and second elements are directly coupled or joined to each other and also includes embodiments in which the first and second elements are indirectly coupled or joined to each other with the addition of one or more other intervening elements.

Further, it is to be understood that the positional or orientational relationships indicated by the terms "front, rear, upper, lower, left, right", "transverse, vertical, horizontal" and "top, bottom" and the like are generally based on the positional or orientational relationships illustrated in the drawings and are provided for convenience in describing the invention and for simplicity in description, and that these terms are not intended to indicate and imply that the referenced devices or elements must be in a particular orientation or be constructed and operated in a particular orientation without departing from the scope of the invention. Also, this application uses specific language to describe embodiments of the application. The terms "inside" and "outside" refer to the inner and outer parts relative to the outline of each part itself, and the terms "first", "second", "third", and the like are used to define the parts, and are used only for the convenience of distinguishing the corresponding parts, and unless otherwise stated, the terms have no special meaning, and therefore, the scope of the present invention should not be construed as being limited. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.

Referring to fig. 1, in an embodiment, the rotor structure of the gas turbine includes an inlet cone 1, an inlet cone rear support ring 2, a balance screw 3, a fan rotor 4, a booster stage rotor 5, a fan shaft 6, and a transmission shaft 7 at an inlet outlet, and when the rotor structure is started, a motor transmits power to the transmission shaft 7 to rotate the fan shaft 6, the fan rotor 4, the booster stage rotor 5, and the like, so as to transmit power to the inlet cone 1, and the entire rotor rotates around a rotation center. The imbalance of the rotor is a main excitation source of the engine, and the working performance and the service life of the engine are directly influenced. And the balance assembly eliminates the vibration to the bearing caused by the fact that centrifugal inertia force cannot be mutually counteracted by adjusting the mass of the balance piece, thereby achieving the balance requirement of the rotor.

Referring to fig. 2 and 3, in one or more embodiments, the balance member of the balance assembly is a balance screw 3, and the balance screw 3 is circumferentially distributed and connected with the intake cone rear support ring 2 through a thread 9. The balance screw 3 is provided with a groove 30 extending from the head end to the tail end, the groove 30 comprises a groove head 10 and a groove body 8 extending from the groove head, the groove head 10 is used for providing a working space for a tool for screwing the balance screw 3, and the groove head 10 is in a hexagon socket shape. And the groove body part 8 is accommodated with a first mass balance piece, and the dynamic balance of the rotor system is adjusted by adjusting the equivalent mass of the first mass balance piece.

The first mass balance member may thus be embodied in the form of an embodiment which is shown with reference to fig. 2, the first mass balance member comprising a filler 11, for example a high temperature healing agent, accommodated inside the body part 8 of the recess. The high-temperature supplement agent is in a paste shape before use, is poured into the groove body part 8, is integrated with the balance screw 3 after being solidified, and can adjust the equivalent mass of the first mass balance piece by adjusting the mass of the added filler, thereby adjusting the dynamic balance of the rotor system. The first mass balance member may also be an embodiment shown in fig. 3, and the first mass balance member includes an external screw 13 fastened to an internal screw structure 12 provided on a side wall of the recessed body portion 8. The mass of each threaded male element 13 can be adjusted (for example, by screwing male elements 13 of different shapes, materials, lengths) or the depth of screwing male elements 13 into female thread structure 12 adjusts the equivalent mass of the first mass balancing element and thus of each balancing screw 3. The external screw member 13 may be a screw structure as shown in fig. 3, but is not limited thereto. Preferably, the internal thread structure 12 and the external thread element 13 are connected by interference fit threads or self-locking threads to strengthen the fastening of the two and prevent the screw from flying out due to the action of centrifugal force in the rotating process. Preferably, the distance L from the tail end of the external screw 13 to the tail end of the balance screw 3 is greater than 8mm, which is advantageous in that the balance screw 3 can be prevented from being pierced by the external screw 13 into which it is screwed when rotated.

It will be appreciated that the first mass balance means may have other forms than the filler 11, the external screw thread 13, for example, and may comprise a pin which is secured to the recess 30 by interference fit with the body portion 8 of the recess. The equivalent mass of each balancing screw 3 is adjusted by adjusting the mass of each interference fit connected pin (e.g. screwing in a pin of different size, material, length), or adjusting the depth of the interference fit connected pin to adjust the equivalent mass of the first mass balance.

Bearing on the above, the beneficial effects that the groove 3 extending from the head end to the tail end of the balance screw 3 is formed in the balance screw 3, and the first mass balance piece is accommodated in the groove body 8 are that the mass balance piece can be filled in the groove of the balance screw 3 under the condition that the external structure and the size of the balance screw 3 are not changed, the equivalent mass of the mass balance piece can be directly adjusted to adjust the dynamic balance of the rotor system, the equivalent mass weight of the balance screw can be adjusted on line in the dynamic balance process, the complicated procedures caused by on-site coping and additional work of the balance screw in the balance process are avoided, and the balance efficiency is effectively improved. In addition, as the external structure size of the balance screw does not need to be changed, only one specification of balance screw needs to be designed in the balance assembly, the processing cost of the balance screw is reduced, and the process procedure is simplified; meanwhile, the design consistency of the balance screw is remarkably improved, only one screw hole specification of the balance screw is needed, the processing error rate is reduced, and the processing efficiency is improved; meanwhile, the design has the advantages of small change on the existing structure, convenient processing and cost saving.

Similarly, referring to fig. 4 and 5, in one or more embodiments, for the balance weight portion of the fan disc disposed in the rotor system, in an embodiment shown in fig. 4, the balance weight portion includes a balance weight body 15, the balance weight body 15 is a combination of a semicircular shape and a square shape, and is provided with a connecting hole 14 and a balance hole 16, the connecting hole 14 is used to fasten a connecting member of the balance weight body 15 and the fan disc 7, the connecting member may be a pin, the pin is in interference fit with the connecting hole, and the connecting member may also be a threaded fastener such as a screw. The balancing holes 16 are used for arranging a second mass balancing member 17 in their interior, the second mass balancing member 17 may also be a screw, a pin and a filler. The dynamic balance adjustment of the rotor system is performed by adjusting the equivalent mass of the second mass balance 17 by screwing in fillers of different shapes, mass screws, pins and different masses.

It is understood that the shapes of the balance weight body, the connecting hole and the balance hole can be selected according to actual conditions. In the embodiment shown in fig. 5, the weight body 19 is square, the size of the connecting hole 18 is larger than that of the balancing hole 20, and the second mass balance member 21 disposed in the balancing hole 20 may be a screw, a pin, and a filler. The dynamic balance adjustment of the rotor system is performed by adjusting the equivalent mass of the second mass balance 21 by screwing in fillers of different shapes, mass screws, pins and different masses. The structure of the balance hole and the structure of the connecting hole can be set to be the same, and the balance hole is easy to process.

Bearing, set up the balancing hole at the balancing piece body and set up the beneficial effect of second mass balance spare inside the balancing hole and lie in, can be under the condition that does not change balancing piece body external structure and size, directly adjust the equivalent mass of mass balance spare and adjust rotor system's dynamic balance, can be at the equivalent mass weight of dynamic balance in-process on-line adjustment balancing piece, avoid need carry out the loaded down with trivial details process that on-the-spot coping, replenishment worker brought to the balancing piece in the balancing process, effectively improved balancing efficiency. In addition, as the external structure size of the balance block does not need to be changed, only one specification of balance block needs to be designed in the balance assembly, the processing cost of the balance block is reduced, and the process procedure is simplified; meanwhile, the design consistency of the balance blocks is remarkably improved, the processing error rate is reduced, and the processing efficiency is improved; meanwhile, the design has the advantages of small change on the existing structure, convenient processing and cost saving.

In summary, in one embodiment, a method of balancing a gas turbine rotor includes the steps of:

arranging balance screws on a rear support ring of an air inlet cone of a rotor system along the circumferential direction, arranging grooves on the balance screws, fixedly arranging first mass balance pieces in the grooves, and balancing the rotor system by adjusting the equivalent mass of the first mass balance pieces; or

The fan disc of the rotor system is provided with a balance block part, the balance block part is provided with a balance hole, a second mass balance piece is fixedly arranged in the balance hole, and the rotor system is balanced by adjusting the equivalent mass of the second mass balance piece.

In particular, the step of adjusting the equivalent mass of the first mass balance may comprise one or more of:

an internal thread structure is arranged on the side wall of the groove, the first mass balance piece comprises an external thread piece, the external thread piece and the internal thread structure are in threaded connection and fastened on the groove, and the equivalent mass is adjusted by adjusting the depth of the external thread piece screwed into the body part of the groove or adjusting the mass of the external thread piece;

the first mass balance piece comprises a filler, the uncured filler is filled into the groove, the filler is integrated with the balance screw after being cured, and the equivalent mass is adjusted by adjusting the mass of the filled filler.

In summary, the beneficial effects of the balance assembly, the balance method, the gas turbine and the rotor system thereof adopting the above embodiments include: under the condition of not changing the external structure and size of the balance screw/balance block, a groove or a balance hole is formed in the balance screw/balance block part of the same specification, and a first mass balance piece or a second mass balance piece is arranged in the groove or the balance hole, so that the number of the balance screws/balance blocks of different specifications required to be arranged in the design process is reduced, the complicated procedures caused by the need of carrying out on-site grinding and adding work on the balance screw in the balance process are avoided, and the balance efficiency is effectively improved. The weight of the balance screw/balance block part is adjusted on line by filling fillers of different materials or screwing screws with different lengths, and the weight of the balance screw/balance block is adjusted in the dynamic balance process, so that the processing cost of the balance screw is reduced, and the process procedure is simplified; meanwhile, the design consistency of the balance screws/balance blocks is remarkably improved, only one type of the specification of the threaded holes of the balance screws/balance blocks is needed, the processing error rate is reduced, and the processing efficiency is improved; meanwhile, the design has the advantages of small change on the existing structure, convenient processing and cost saving. The balance performance of the rotor system is improved, and the overall working performance and service life of the gas turbine are improved.

Although the present invention has been disclosed in the above-mentioned embodiments, it is not intended to limit the present invention, and those skilled in the art may make variations and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.

Claims

1. A balancing assembly for balancing a rotor system of a gas turbine, comprising a balancing screw for circumferentially connecting an inlet cone rear support ring of the rotor system, the balancing screw having a recess extending from a head end thereof to a tail end thereof, the recess comprising a recess head and a recess body extending from the recess head, the recess body accommodating a first mass balancing member; under the condition that the external structure and the size of the balance screw are not changed, the equivalent mass of the first mass balance piece is directly adjusted to adjust the dynamic balance of the rotor system, and the equivalent mass of the balance screw can be adjusted on line in the dynamic balance process.

2. The balance assembly of claim 1, wherein the side wall of the pocket body portion includes an internal thread formation, and the first mass balance member includes an external threaded member threadably secured to the pocket by the external threaded member and the internal thread formation.

3. The balance assembly of claim 2, wherein the tail end of the external threaded member is spaced from the tail end of the balance screw by a distance greater than 8 mm.

4. The counterbalance assembly of claim 1, wherein the first mass balance member includes a filler contained within the body portion of the recess.

5. The counterbalance assembly of claim 1, wherein the first mass balance includes a pin secured to the recess by an interference fit connection with the body portion of the recess.

6. A rotor system for a gas turbine, comprising a balancing assembly according to any one of claims 1 to 5.

7. A gas turbine engine comprising the rotor system of claim 6.

8. A method of balancing a rotor system of a gas turbine,

arranging balance screws on a rear support ring of an air inlet cone of a rotor system along the circumferential direction, arranging grooves on the balance screws, fixedly arranging first mass balance pieces in the grooves, and balancing the rotor system by adjusting the equivalent mass of the first mass balance pieces; under the condition that the external structure and the size of the balance screw are not changed, the equivalent mass of the first mass balance piece is directly adjusted to adjust the dynamic balance of the rotor system, and the equivalent mass of the balance screw can be adjusted on line in the dynamic balance process.

9. The balancing method of claim 8,

adjusting the equivalent mass of the first mass balance by one or more of: