CN215334124U

CN215334124U - Squeeze film damper and aircraft engine

Info

Publication number: CN215334124U
Application number: CN202120586889.1U
Authority: CN
Inventors: 陈亚龙; 马会防; 何春亮
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-03-23
Filing date: 2021-03-23
Publication date: 2021-12-28
Anticipated expiration: 2031-03-23

Abstract

The present disclosure provides a squeeze film damper, comprising: an elastic support 1; the radial inner circumferential surface of one end of the amplitude limiter 2 is in clearance fit with the radial outer circumferential surface of one end of the elastic support 1 to form a matching section; and sealing ring 3, set up in the both ends of cooperation section, cooperation section and sealing ring 3 form damping chamber C, are filled with damping fluid in the damping chamber C, and the radial outside of sealing ring 3 is provided with recess 30, and the circumferential surface in the radial outside of sealing ring 3 keeps in contact with amplitude limiter 2 and recess 30 and amplitude limiter 2 form the enclosure space with sealed damping chamber C. This disclosure can promote the damping effect of squeeze film damper through improving the sealed effect of crowded sealing face.

Description

Squeeze film damper and aircraft engine

Technical Field

The disclosure relates to the technical field of damping vibration attenuation, in particular to an extrusion oil film damper and an aircraft engine.

Background

The operating speed of the aircraft engine rotor is usually higher than the critical speed of the rotor, which is required to pass during the start-stop process. The magnitude of the vibration of the rotor through the critical speed is affected by damping in addition to the load (e.g., unbalance). Generally, increasing the damping of the rotor system can reduce the vibration response of the rotor when the rotor passes through the critical speed, and therefore, a squeeze film damper is often arranged at a bearing of the rotor system to increase the damping of the rotor system, reduce the amplitude of the rotor when the rotor passes through the critical speed, and avoid the excessive vibration of the rotor.

The squeeze oil film refers to an oil film in a gap defined by the elastic support, the sealing ring and the amplitude limiter. In the operation process of the aircraft engine, the amplitude limiter has small vibration displacement, the elastic support has large vibration displacement, and an oil film between the amplitude limiter and the elastic support is extruded to generate a damping effect. The damping effect of the squeeze film damper is in a large relation with the end sealing condition of the squeeze film damper, if the sealing performance of the end of the squeeze film damper is poor, oil is easy to leak from a sealing surface of an oil film positive pressure area when the squeeze film damper works, air is easy to suck from a sealing surface of an oil film negative pressure area, and the damping effect of the squeeze film damper is affected.

SUMMERY OF THE UTILITY MODEL

The purpose of this disclosure is to provide an extrusion film damper and aeroengine, through improving the sealed effect of crowded sealing face, promotes the damping effect of extrusion film damper.

A first aspect of the present disclosure provides a squeeze film damper comprising:

an elastic support;

the circumferential surface of the radial inner side of one end of the amplitude limiter is in clearance fit with the circumferential surface of the radial outer side of one end of the elastic support to form a matching section; and

the sealing ring set up in the both ends of cooperation section, the cooperation section with the sealing ring forms the damping chamber, the damping intracavity is full of damping liquid, the radial outside of sealing ring is provided with the recess, the radial outside of sealing ring the circumferential surface with the amplitude limiter keep in touch just the recess with the amplitude limiter forms the enclosure space in order to seal the damping chamber.

According to some embodiments of the disclosure, the groove extends in a circumferential direction of the seal ring.

According to some embodiments of the disclosure, the seal ring has one of the grooves.

According to some embodiments of the present disclosure, the seal ring has a plurality of the grooves arranged side by side in an axial direction of the seal ring.

A second aspect of the present disclosure provides an aircraft engine comprising a squeeze film damper according to the first aspect of the present disclosure.

According to the squeeze film damper provided by the embodiment of the disclosure, the radial outer side of the sealing ring is provided with the groove. The arrangement of the groove can reduce the axial contact length of the sealing ring and the amplitude limiter along the sealing ring, and increase the average contact pressure of the sealing ring and the amplitude limiter so as to improve the sealing effect of the sealing surface. In the setting area of recess, recess and amplitude limiter form the enclosure space, and damping fluid infiltration just fills up after the enclosure space, can increase the axial flow resistance of squeeze film along the cooperation section, can form one at least sealed along the axial of cooperation section, reduces the sealed effect of leaking in order to promote sealed face of squeeze film damper. As the sealing effect of the squeeze film damper is improved, the damping effect of the squeeze film damper is also improved. Based on the better damping effect of the squeeze film damper, the vibration response of the rotor of the aircraft engine provided by the disclosure when the rotor passes through the critical rotating speed can be reduced.

Other features of the present disclosure and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the disclosure and together with the description serve to explain the disclosure and not to limit the disclosure. In the drawings:

FIG. 1 is a schematic structural view of a squeeze film damper according to some embodiments of the present disclosure.

FIG. 2 is a partially enlarged schematic view of a squeeze film damper according to some embodiments of the present disclosure.

FIG. 3 is an enlarged schematic view of the squeeze film damper of FIG. 2 at the seal ring.

Fig. 4 is a schematic cross-sectional view of the seal ring shown in fig. 3.

FIG. 5 is a schematic view of a partial enlarged structure of a squeeze film damper according to further embodiments of the present disclosure.

FIG. 6 is a schematic structural view of a seal ring at an interface according to some embodiments of the present disclosure.

In fig. 1 to 6, each reference numeral represents:

1. an elastic support; 2. an amplitude limiter; 20. an oil supply hole; 3. a seal ring; 30. a groove; 31. a hook interface; 4. a bearing; s1, a first sealing surface; s2, a second sealing surface; C. a damper chamber.

Detailed Description

The technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure, and it is obvious that the described embodiments are only a part of the embodiments of the present disclosure, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the disclosure, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.

The relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present disclosure unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

In the description of the present disclosure, it should be understood that the terms "first", "second", etc. are used to define the components, and are used only for convenience of distinguishing the corresponding components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present disclosure.

In the description of the present disclosure, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are presented only for the convenience of describing and simplifying the disclosure, and in the absence of a contrary indication, these directional terms are not intended to indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the disclosure; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

As shown in fig. 1 to 6, some embodiments of the present disclosure provide a squeeze film damper including an elastic support 1, a limiter 2, and a seal ring 3. The radial inner circumferential surface of one end of the amplitude limiter 2 is in clearance fit with the radial outer circumferential surface of one end of the elastic support 1 to form a matching section. The radially inner axial surface of the elastic support 1 at the engagement section is intended to engage with the bearing 4. The sealing rings 3 are arranged at both ends of the matching section. The matching section and the sealing ring 3 form a damping cavity C, and the damping cavity C is filled with damping liquid to form an extrusion oil film. The limiter 2 is provided with an oil supply hole 20 for filling the damping fluid. The radially outer side of the seal ring 3 is provided with a groove 30, the circumferential surface of the radially outer side of the seal ring 3 is held in contact with the limiter 2 and the groove 30 forms a closed space with the limiter 2 to seal the damper chamber C.

As shown in fig. 3 and 5, the seal ring 3 is mounted in the mounting groove of the elastic support 1, a contact area of the seal ring 3 with the limiter 2 constitutes a first sealing surface S1, and a contact area of the seal ring 3 with the mounting groove constitutes a second sealing surface S2. The seal ring 3 seals the damper chamber C by the first seal surface S1 and the second seal surface S2. The sealing effect of the sealing ring 3 on the damping chamber C is influenced by the contact pressure on the first sealing surface S1 and the contact pressure on the second sealing surface S2, wherein the contact pressure on the first sealing surface S1 is mainly derived from the elastic force of the sealing ring 3, the direction of which is in the radial direction of the sealing ring 3.

When the elastic force of the seal ring 3 mounted in the mounting groove in the radial direction is F, the contact length of the seal ring 3 and the limiter in the axial direction of the seal ring 3 is L, and the outer diameter of the seal ring 3 mounted in the mounting groove is D, the average contact pressure δ on the first seal surface S1 is F/(LD). It follows that if the average contact pressure on the first sealing surface S1 is insufficient, the sealing effect of the first sealing surface S1 also decreases, resulting in a decrease in the damping effect of the squeeze film damper. By properly reducing the contact length L of the seal ring 3 and the limiter in the axial direction of the seal ring 3, the average contact pressure δ on the first seal surface S1 can be increased, and the sealing effect of the seal surface can be improved.

According to the squeeze film damper provided by the embodiment of the disclosure, the radial outer side of the sealing ring is provided with the groove. The arrangement of the groove can reduce the axial contact length of the sealing ring and the amplitude limiter along the sealing ring, and increase the average contact pressure of the sealing ring and the amplitude limiter so as to improve the sealing effect of the sealing surface. In the setting area of recess, recess and amplitude limiter form the enclosure space, and damping fluid infiltration just fills up after the enclosure space, can increase the axial flow resistance of squeeze film along the cooperation section, can form one at least sealed along the axial of cooperation section, reduces the sealed effect of leaking in order to promote sealed face of squeeze film damper. As the sealing effect of the squeeze film damper is improved, the damping effect of the squeeze film damper is also improved.

In some embodiments, the groove 30 extends in the circumferential direction of the sealing ring 3.

As shown in fig. 5, in some embodiments, the sealing ring 3 has one groove 30.

To further enhance the damping effect of squeeze film dampers, as shown in fig. 2-4, in some embodiments, the seal ring 3 has a plurality of grooves 30 disposed side by side in the axial direction of the seal ring 3. The plurality of grooves 30 form a plurality of closed spaces with the limiter 2, forming a plurality of seals in the axial direction of the mating segment. The contact length L of the seal ring 3 and the limiter in the axial direction of the seal ring 3 is (L1+ L2+ L3+ L4), and the larger the number of the grooves 30, the smaller the contact length L, and the larger the average contact pressure δ on the first seal surface S1. The pressure of the squeeze film in the damping cavity C is set to be P, and due to the flow resistance among the closed spaces, after passing through the closed space formed by the grooves 30, the pressure of the squeeze film is gradually reduced to P1, P2 and P3 until the atmospheric pressure is P0, so that the leakage of the damping liquid can be reduced.

As shown in fig. 6, in some embodiments, the interface of the seal ring 3 may employ a hook interface 31. In some embodiments, not shown, the interface of the sealing ring 3 may also be a stepped interface.

Some embodiments of the present disclosure also provide an aircraft engine comprising the aforementioned squeeze film damper. Based on the better damping effect of the squeeze film damper, the vibration response of the rotor of the aircraft engine passing through the critical rotating speed can be reduced.

Finally, it should be noted that: the above examples are intended only to illustrate the technical solutions of the present disclosure and not to limit them; although the present disclosure has been described in detail with reference to preferred embodiments, those of ordinary skill in the art will understand that: modifications to the embodiments of the disclosure or equivalent replacements of parts of the technical features may be made, which are all covered by the technical solution claimed by the disclosure.

Claims

1. A squeeze film damper, comprising:

an elastic support (1);

the radial inner circumferential surface of one end of the amplitude limiter (2) is in clearance fit with the radial outer circumferential surface of one end of the elastic support (1) to form a matching section; and

sealing ring (3), set up in the both ends of cooperation section, the cooperation section with sealing ring (3) form damping chamber (C), be full of damping fluid in damping chamber (C), the radial outside of sealing ring (3) is provided with recess (30), the circumferential surface in the radial outside of sealing ring (3) with limiter (2) keep in contact just recess (30) with limiter (2) form the enclosure space in order to seal damping chamber (C).

2. Squeeze film damper according to claim 1, characterized in that the groove (30) extends in the circumferential direction of the sealing ring (3).

3. Squeeze film damper according to claim 1, characterized in that said sealing ring (3) has one said groove (30).

4. Squeeze film damper according to claim 1, characterized in that the sealing ring (3) has a plurality of said grooves (30) arranged side by side in the axial direction of the sealing ring (3).

5. An aircraft engine comprising a squeeze film damper according to any one of claims 1 to 4.