阅读说明：本技术 一种航空发动机气门推杆套管和气门推杆机构 (Aero-engine valve push rod sleeve and valve push rod mechanism ) 是由 陈聪明 于 2019-11-27 设计创作，主要内容包括：本发明提供一种航空发动机气门推杆套管以及具有该套管的航空发动机气门推杆机构,航空发动机气门推杆套管包括第一套管、第二套管和弹性件,所述第一套管可滑动且密封套设于第二套管内,所述弹性件作用于第一套管和第二套管并对第一套管和第二套管施加一相互远离的作用力。在推杆外套接该航空发动机气门推杆套管,能够很好的隔离保护推杆,且第一套管和第二套管在弹性件的作用下能够自适应的抵压于发动机机体和气缸盖上,不会影响正常运作。同时,其中空结构可用于润滑油的流通,使推杆以及推杆的连接结构能够得到充分的润滑。(The invention provides an aero-engine valve push rod sleeve and an aero-engine valve push rod mechanism with the same. This aeroengine valve push rod sleeve pipe is cup jointed outward to the push rod, isolation protection push rod that can be fine, and first sleeve pipe and second sleeve pipe can be the self-adaptation under the effect of elastic component support press on engine organism and cylinder head, can not influence normal operating. Meanwhile, the hollow structure can be used for circulating lubricating oil, so that the push rod and the connecting structure of the push rod can be fully lubricated.)

1. The utility model provides an aeroengine valve push rod sleeve pipe which characterized in that: the elastic piece acts on the first sleeve and the second sleeve and exerts an acting force which is far away from each other on the first sleeve and the second sleeve.

2. The aero engine valve push rod bushing of claim 1 wherein: the first sleeve is provided with an annular groove on the peripheral side wall, a sealing ring is sleeved in the annular groove, the first sleeve can slide through the sealing ring, and the sealing sleeve is arranged in the second sleeve.

3. The aero engine valve push rod bushing of claim 2 wherein: the annular grooves in the peripheral side wall of the first sleeve are provided with a plurality of annular grooves, and the sealing rings are sleeved in the annular grooves.

4. The aero engine valve push rod bushing of claim 2 wherein: two protruding parts protrude from the peripheral side wall of the first sleeve, and the two protruding parts are arranged at intervals and jointly surround the annular groove.

5. The aero engine valve push rod bushing of claim 1 wherein: the elastic piece is arranged in the second sleeve.

6. The aero engine valve push rod bushing of claim 5 wherein: the elastic piece is a spring, and two ends of the spring are respectively abutted to the first sleeve and the second sleeve.

7. The aero engine valve push rod bushing of claim 1 wherein: the first sleeve and the second sleeve are made of steel.

8. The aero engine valve push rod bushing of claim 1 wherein: the first sleeve is provided with a protruding part protruding from the peripheral side wall of the outer end part.

9. The aero engine valve push rod bushing of claim 1 wherein: the second sleeve is provided with an inward-contracting step part at the outer end part.

10. An aircraft engine valve push rod mechanism comprises a push rod, wherein one end of the push rod is matched with a tappet of an engine, and the other end of the push rod is matched with a valve rocker; the method is characterized in that: the valve push rod sleeve of the aircraft engine is characterized by further comprising a sleeve, the sleeve is the valve push rod sleeve of the aircraft engine as claimed in any one of claims 1 to 9, the sleeve is movably sleeved outside the push rod, the outer end portion of the first sleeve and the outer end portion of the second sleeve are respectively pressed against an engine body and a cylinder cover through the acting force of an elastic piece, and the engine body, the sleeve and the cylinder cover are combined to form a communicated lubricating oil circulation channel.

Technical Field

The invention relates to the field of aero-engines, in particular to an aero-engine valve push rod sleeve and an aero-engine valve push rod mechanism with the sleeve.

Background

The existing engine valve actuating mechanism is composed of parts such as a valve, a rocker arm, a push rod, a tappet, a camshaft and the like. One end of the push rod is matched with the tappet, and the other end of the push rod is matched with the valve rocker, so that transmission connection is formed. However, in the field of four-stroke piston type aircraft engines, due to structural design or assembly requirements and other reasons, the push rod is located outside the cylinder body, and although the push rod can play a role in transmission, the push rod is lack of protection, and the connecting structure of the push rod and the outside cannot be well lubricated, so that the push rod is fast in abrasion, short in service life and high in safety risk. If the push rod is integrated inside like an engine in other fields such as automobiles, the existing structure needs to be reformed again, which increases the weight and cost.

Disclosure of Invention

Therefore, the structure is improved on the basis that the push rod of the existing four-stroke piston type aircraft engine is exposed, the structure which can protect the push rod and can meet the circulation of lubricating oil is obtained, and the problems can be well solved.

In order to achieve the purpose, the technical scheme provided by the invention is as follows:

the utility model provides an aeroengine valve push rod sleeve pipe, includes first sleeve pipe, second sleeve pipe and elastic component, first sleeve pipe slidable and seal cover locate in the second sleeve pipe, the elastic component acts on first sleeve pipe and second sleeve pipe and exerts the effort that keeps away from each other to first sleeve pipe and second sleeve pipe.

Furthermore, an annular groove is formed in the peripheral side wall of the first sleeve, a sealing ring is sleeved in the annular groove, the first sleeve can slide through the sealing ring, and the sealing sleeve is arranged in the second sleeve.

Furthermore, a plurality of annular grooves are formed in the peripheral side wall of the first sleeve, and the sealing rings are sleeved in the annular grooves.

Furthermore, two protruding parts protrude from the peripheral side wall of the first sleeve, and the two protruding parts are arranged at intervals and jointly surround the annular groove.

Further, the elastic piece is arranged in the second sleeve.

Furthermore, the elastic part is a spring, and two ends of the spring respectively abut against the first sleeve and the second sleeve.

Furthermore, the first sleeve and the second sleeve are made of steel.

Furthermore, the second sleeve is provided with an inward-contracting step part at the outer end part.

Furthermore, the first sleeve is convexly provided with an abutting convex part on the peripheral side wall of the outer end part.

An aircraft engine valve push rod mechanism comprises a push rod, wherein one end of the push rod is matched with a tappet of an engine, and the other end of the push rod is matched with a valve rocker; the valve push rod sleeve of the aircraft engine is characterized by further comprising a sleeve, the sleeve is the valve push rod sleeve of the aircraft engine, the sleeve is movably sleeved outside the push rod, the outer end portion of the first sleeve and the outer end portion of the second sleeve are respectively abutted to the engine body and the cylinder cover through the acting force of the elastic piece, and the engine body, the sleeve and the cylinder cover are combined to form a communicated lubricating oil circulation channel.

Through the technical scheme provided by the invention, the method has the following beneficial effects:

the sleeve (being the aero-engine valve push rod sleeve) is sleeved outside the exposed push rod, the sleeve can well isolate and protect the push rod, the first sleeve and the second sleeve of the sleeve can be self-adaptively supported and pressed on the engine body and the cylinder cover under the action of the elastic piece, and the self-adaptive change can be realized along with the small change of the relative positions of the engine body and the cylinder cover, so that the normal operation can not be influenced. Meanwhile, a lubricating oil circulation channel formed by combining the engine body, the sleeve and the cylinder cover can be used for circulating lubricating oil, so that a connecting structure of the push rod and the push rod can be fully lubricated, the action is smoother, the fault is not easy to occur, the safety is better, and the service life is longer; and the structure is simple, the structure is only added on the original structure, the large-scale transformation is not needed, and the realization is easy.

Drawings

FIG. 1 is a perspective view of the appearance of a valve push rod sleeve of an aircraft engine in an embodiment;

FIG. 2 is an exploded view of an aircraft engine valve push rod sleeve according to an embodiment;

FIG. 3 is a sectional view of an aircraft engine valve push rod sleeve according to an embodiment;

FIG. 4 is a schematic external view of a valve push rod sleeve and a push rod of an aircraft engine in an embodiment after being matched;

FIG. 5 is a cross-sectional view of an aircraft engine valve push rod sleeve and a push rod after being engaged in an embodiment.

Detailed Description

To further illustrate the various embodiments, the invention provides the accompanying drawings. The accompanying drawings, which are incorporated in and constitute a part of this disclosure, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the embodiments. Those skilled in the art will appreciate still other possible embodiments and advantages of the present invention with reference to these figures. Elements in the figures are not drawn to scale and like reference numerals are generally used to indicate like elements.

The invention will now be further described with reference to the accompanying drawings and detailed description.

Referring to fig. 1 to 3, the present embodiment provides an aircraft engine valve push rod bushing, which includes a first bushing 10, a second bushing 20, and an elastic member 30, wherein the first bushing 10 is slidably and hermetically sealed inside the second bushing 20, and the elastic member 30 acts on the first bushing 10 and the second bushing 20 and applies a force to the first bushing 10 and the second bushing 20 to move away from each other.

The aero-engine valve push rod sleeve is used in the structure of an aero-engine valve push rod, as shown in fig. 4 and 5, the sleeve (namely, the aero-engine valve push rod sleeve) can be sleeved outside a push rod 1 connected between a tappet and a valve rocker of an engine, so that the function of isolating and protecting the push rod 1 is realized; and the first sleeve 10 and the second sleeve 20 of the sleeve can be self-adaptively pressed on the engine body and the cylinder cover under the action of the elastic part 30, and can be self-adaptively changed along with the slight change of the relative position of the engine body and the cylinder cover, and the sleeve is always kept sealed, so that the normal operation is not influenced, and the applicability is good. Meanwhile, a hollow sealing pipeline formed by the first sleeve 10 and the second sleeve 20 can be used for circulating lubricating oil, so that the push rod 1 and a connecting structure of the push rod 1 can be fully lubricated, the action is smoother, the fault is not easy to occur, the safety is better, and the service life is longer; and the structure is simple, the structure is only added on the original structure, the large-scale transformation is not needed, and the realization is easy.

Further, in this embodiment, the elastic member 30 is disposed in the second sleeve 20, so that the elastic member 30 can be covered and protected by the first sleeve 10 and the second sleeve 20, and is not easily damaged. Of course, in other embodiments, the elastic member 30 may be disposed outside the first sleeve 10 or the second sleeve 20, or the like, if the space inside the second sleeve 20 is insufficient or the second sleeve 20 is assembled.

Furthermore, in this embodiment, the elastic member 30 is a spring, two ends of the spring 30 respectively abut against the first sleeve 10 and the second sleeve 20, the spring 30 has a simple structure and is easy to obtain, and the spring 30 is also a hollow structure, so that a space through which the push rod 1 is inserted can be provided, and the action of the push rod 1 is not interfered. Of course, in other embodiments, the elastic member 30 may be other devices capable of applying a force to separate the first sleeve 10 and the second sleeve 20 from each other.

Furthermore, in this embodiment, an annular groove 101 is formed in a peripheral side wall of the first sleeve 10, a seal ring 40 is sleeved in the annular groove 101, the first sleeve 10 is slidably arranged in the second sleeve 20 through the seal ring 40 in a sealing manner, and the sealing structure is simple and has good sealing performance.

More specifically, the annular grooves 101 on the peripheral side wall of the first sleeve 10 are provided with a plurality of annular grooves 101, and the sealing rings 40 are sleeved in the annular grooves 101, so that the sealing effect is achieved, multiple sealing is realized, and the sealing effect is better. Simultaneously, adopt the sealed complex structure of multiunit, also play the effect of the sliding guide of first sleeve pipe 10 and second sleeve pipe 20, effectively prevent that first sleeve pipe 10 and second sleeve pipe 20 from producing the slope skew. In this embodiment, there are two sets of matching structures of the annular groove 101 and the sealing ring 40. Of course, other numbers of sets may be provided in other embodiments.

Further, in this embodiment, two protruding portions 11 protrude from the peripheral side wall of the first sleeve 10, and the two protruding portions 11 are disposed at intervals and jointly enclose the annular groove 101; wherein, spring 30 cup joints on first sleeve 10 and contradicts on bellying 11 with first sleeve 10 complex tip for bellying 11 plays the effect of enclosing into ring channel 101 and being used for contradicting spring 30 simultaneously, and structural design is ingenious, and the program for processing is few. Of course, in other embodiments, the structure surrounding the annular groove 101 and the structure for abutting against the spring 30 may be provided separately.

Furthermore, in this embodiment, the first sleeve 10 and the second sleeve 20 are made of steel, which has good hardness, stable structure, low cost and easy access. Of course, in other embodiments, other materials, such as metal alloys, may be used.

Further, in this embodiment, the second sleeve 20 is provided with an inward-contracting step portion 21 at the outer end portion, the second sleeve 20 is inserted into the engine body or the cylinder head at the outer end portion, and is pressed and limited by the step portion 21, and meanwhile, the inner wall of the inward-contracting step portion 21 can also be used for abutting against the spring 30, so that the assembly of the spring 30 is realized, and the structural design is ingenious.

Further, in the present embodiment, the first sleeve 10 is provided with an interference protrusion 12 protruding on the peripheral side wall of the outer end position. During assembly, the first sleeve 10 is inserted into a cylinder cover or an engine body at the outer end part and is abutted and limited by the abutting convex part 12, so that assembly is completed, and the structure is simple.

Referring to fig. 4 and 5, the present embodiment further provides an aircraft engine valve push rod mechanism, which includes a push rod 1 and a sleeve, wherein one end of the push rod 1 is engaged with a tappet of an engine, and the other end is engaged with a valve rocker, specifically, the arrangement of the push rod 1 is the prior art, and the specific engagement structure thereof is already known and is well-used by those skilled in the art, and will not be described in detail herein. The sleeve is the aero-engine valve push rod sleeve, the sleeve is movably sleeved outside the push rod 1, namely, the sleeve is in clearance sleeve joint, the outer end part of the first sleeve 10 and the outer end part of the second sleeve 20 are respectively pressed against an engine body and a cylinder cover through the acting force of the elastic part 30, and the engine body, the sleeve and the cylinder cover are combined to form a communicated lubricating oil circulation channel.

The exposed push rod 1 is sleeved with a sleeve (namely an aero-engine valve push rod sleeve), the sleeve can well isolate and protect the push rod 1, the first sleeve 10 and the second sleeve 20 of the sleeve can be self-adaptively pressed on an engine body and a cylinder cover under the action of the elastic piece 30, and the normal operation cannot be influenced by the self-adaptive change along with the slight change of the relative positions of the engine body and the cylinder cover. Meanwhile, a lubricating oil circulation channel formed by combining the engine body, the sleeve and the cylinder cover can be used for circulating lubricating oil, so that the push rod 1 and a connecting structure of the push rod 1 can be fully lubricated, the action is smoother, the fault is not easy to occur, the safety is better, and the service life is longer; and the structure is simple, the structure is only added on the original structure, the large-scale transformation is not needed, and the realization is easy.

While the invention has been particularly shown and described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.