CN215213680U - Combined rotor for aviation rotor engine - Google Patents

Abstract

The utility model discloses a combined rotor for an aero-rotor engine, which comprises a triangular rotor body, wherein three top ends of the triangular rotor body are respectively provided with a rotor body sealing groove, the outer side of the triangular rotor body is provided with three detachable working face rotor sleeves, and the three working face rotor sleeves correspond to three sides of the triangular rotor body; the top and the bottom of the triangular rotor body are respectively provided with a detachable end face rotor sleeve, the outer edge of the end face rotor sleeve is similar to the outer edge of the triangular rotor body in shape, the center of the end face rotor sleeve is of a hollow structure, the hollow structure in the center of the end face rotor sleeve corresponds to the hollow structure in the center of the triangular rotor body, and three top ends of the end face rotor sleeve are respectively provided with an end face rotor sleeve sealing groove matched with the rotor body sealing groove; the clearance between the working face rotor sleeve and the end face rotor sleeve forms an end face seal groove. The utility model provides a current rotor engine quality great, the lower problem of merit weight to improve its maintainability.

Description

Combined rotor for aviation rotor engine

Technical Field

The utility model relates to a triangle rotary engine technical field especially relates to an aviation is combination formula rotor for rotary engine.

Background

The aircraft engine is the heart of an aircraft, restricts the flight performance of the aircraft, and is the key influencing the development of the aviation industry. Engineers continue to seek breakthrough in the aspects of improving engine power, thrust-weight ratio, maintainability and the like, and rotary engines have great advantages in the field of aviation, particularly unmanned aerial vehicles, by virtue of the characteristics of light weight, low noise, small volume, high output power and the like. The unmanned aerial vehicle can be rapidly developed towards the aspects of miniaturization, long endurance, more economy in manufacturing and maintenance and the like.

The rotor of current aviation rotor engine often adopts the integral type, mostly come by cast iron integrated into one piece processing, its advantage is that can satisfy the requirement of wear-resisting high temperature resistant and intensity, but the limitation is, the structure of whole cast iron has increased the weight of rotor on the one hand, on the other hand has increased the weight that is used for the balancing weight piece of keep balance, make the whole quality of engine big, the engine power-weight ratio has been reduced, it is too big to make the aircraft bear a burden, load is low excessively, secondly the engine is when maintaining and part is changed, the whole change of part causes the waste. Among the current patent, in the utility model with publication number CN200961507, disclosed a triangle rotor engine's sectional type rotor device, the device is with the terminal surface part of rotor and front and back end cover integration, and its advantage has reduced the weight of rotor, has simplified processing technology, reduce cost, and its limitation has aggravated the friction between rotor and the end cover, and the rotor hollowing part's intensity can't be guaranteed, and the maintainability is low.

Disclosure of Invention

To the problem that exists, the utility model aims at providing an aerorotor is combination formula rotor for engine has solved the great, lower problem of merit of current rotor engine quality to improve its maintainability.

In order to achieve the above object, the utility model adopts the following technical scheme:

the utility model provides a combination formula rotor for aerorotor engine, includes the triangle rotor body, the three top department of triangle rotor body all is equipped with rotor body seal groove, its characterized in that: three detachable working face rotor sleeves are arranged on the outer side of the triangular rotor body, and correspond to three side faces of the triangular rotor body; the triangular rotor comprises a triangular rotor body, a rotor cover and a rotor cover, wherein the top and the bottom of the triangular rotor body are respectively provided with a detachable end face rotor cover, the outer edge of the end face rotor cover is of a triangular structure with a shape similar to that of the outer edge of the triangular rotor body, the center of the end face rotor cover is of a hollow structure, the hollow structure in the center of the end face rotor cover corresponds to the hollow structure in the center of the triangular rotor body, and three top ends of the end face rotor cover are respectively provided with an end face rotor cover sealing groove matched with the rotor body sealing groove;

and a gap between the working face rotor sleeve and the end face rotor sleeve forms an end face sealing groove.

Furthermore, each working face rotor sleeve is provided with first threaded holes close to two ends, three side faces of the triangular rotor body are provided with second threaded holes corresponding to the first threaded holes, and the first threaded holes are connected with the second threaded holes through screws.

Furthermore, three top department of terminal surface rotor cover all is equipped with two third screw holes, two the third screw hole is located the both sides rather than the terminal surface rotor cover seal groove that corresponds respectively, all be equipped with on the top surface of triangle rotor body and the bottom surface with third screw hole assorted fourth screw hole, the third screw hole with also pass through screwed connection between the fourth screw hole.

Furthermore, a long strip-shaped through hole is formed in the center of the working face rotor sleeve.

The utility model has the advantages that: compared with the prior art, the utility model has the improvement that,

1. the combined rotor for the aviation rotor engine utilizes the triangular rotor of the existing rotor engine, on the basis, two parts of components of the working face rotor sleeve and the end face rotor sleeve are added, and detachable connecting structures are respectively arranged between the working face rotor sleeve and the triangular rotor body as well as between the end face rotor sleeve and the triangular rotor body, so that a set of combined rotor is formed; the working face rotor sleeve is made of high-temperature-resistant materials, so that the combined rotor can meet the requirement of stable operation when bearing the impact of gas explosion pressure under the high-temperature working condition of a combustion chamber, and is more reliable; the end face rotor sleeve is made of wear-resistant materials, so that the combined rotor can effectively deal with friction between the end face and the end cover during working, the wear-resistant requirement is met, and the sealing performance and the reliability are improved. The triangular rotor body can be made of materials and reduce weight, so that the structure is reasonable, the rotor is more durable, the thrust-weight ratio of the engine is improved, and the service life of the engine is prolonged.

2. The utility model discloses a combined rotor triangular rotor body's for aerorotor engine most advanced and cylinder body linear contact, triangular rotor body's terminal surface and terminal surface rotor cover contact all can produce the friction in the course of the work, consequently, working face rotor cover and terminal surface rotor cover adopt wear-resisting material can improve triangular rotor body's wear resistance, prolong triangular rotor body, cylinder body and terminal surface rotor cover's life.

3. The utility model discloses a combination formula rotor can bear gas explosion pressure at the inflation in-process of igniteing, and the triangle rotor body can use high strength light material, when making it reach its wear-resisting requirement, has improved more fragile rotor waist intensity.

4. Compare in current rotor engine life-span low, it is heavy to maintain the task, the utility model discloses a combination formula rotor of telescopic structure can be so that only reach the purpose of maintaining the engine through changing working face rotor cover and terminal surface rotor cover, and the assembly is simple, reduces technology complexity, and material saving improves economic nature.

Drawings

Fig. 1 is a schematic view of the combined rotor structure of the present invention.

Fig. 2 is a partially enlarged view of a portion a in fig. 1 according to the present invention.

Fig. 3 is an exploded view of the composite rotor of the present invention.

Fig. 4 is the schematic structural diagram of the triangular rotor body of the present invention.

Fig. 5 is a schematic structural view of the working face rotor sleeve of the present invention.

Fig. 6 is a schematic structural view of the end face rotor sleeve of the present invention.

Wherein: the rotor comprises a 1-triangular rotor body, a 2-rotor body sealing groove, a 3-working face rotor sleeve, a 4-end face rotor sleeve, a 5-end face rotor sleeve sealing groove, a 6-end face sealing groove, a 7-first threaded hole, a 8-second threaded hole, a 9-third threaded hole, a 10-fourth threaded hole, a 11-screw and a 12-through hole.

Detailed Description

In order to make those skilled in the art better understand the technical solution of the present invention, the following describes the technical solution of the present invention with reference to the accompanying drawings and embodiments.

Referring to the combined rotor for the aerorotor engine shown in the attached drawings 1-6, the combined rotor comprises a triangular rotor body 1, the triangular rotor body 1 adopts the existing triangular rotor for the aerorotor engine, and comprises an inner gear and a needle bearing, the details are not repeated here, three top ends of the triangular rotor body 1 are respectively provided with a rotor body sealing groove 2, a sealing strip made of metal is arranged in the rotor body sealing groove 2, and the part adopts the existing sealing groove structure and the sealing strip.

Furthermore, three detachable working face rotor sleeves 3 are arranged on the outer side of the triangular rotor body 1, and the three working face rotor sleeves 3 are integrally arc-shaped and correspond to three side faces of the triangular rotor body 1; the working face rotor sleeve 3 is attached to and arranged outside the side wall of the triangular rotor body 1 corresponding to the working face rotor sleeve. Specifically, each working face rotor sleeve 3 is provided with first threaded holes 7 near two ends, three side faces of the triangular rotor body 1 are provided with second threaded holes 8 corresponding to the first threaded holes 7, and the first threaded holes 7 are connected with the second threaded holes 8 through screws 11. Working face rotor cover 3 adopts high temperature resistant material for the combined rotor in this application can satisfy the demand of stable work when bearing gas explosion pressure and assault under the combustion chamber high temperature operating condition, makes it more reliable.

Further, the top and the bottom of triangle rotor body 1 all are equipped with detachable end face rotor cover 4, the outward flange of end face rotor cover 4 be with the similar triangle-shaped structure of triangle rotor body 1 outward flange shape, just the outward flange of end face rotor cover 4 with the outward flange of triangle rotor body 1 leaves certain distance to make and form certain clearance between working face rotor cover 3 and the end face rotor cover 4 when the assembly, working face rotor cover 3 with clearance between the end face rotor cover 4 is end face seal groove 6, also be provided with the sealing strip of metal in the end face seal groove 6 (adopt current metal sealing strip can, not shown in the figure), realize end face seal. The center of the end face rotor sleeve 4 is of a hollow structure, the hollow structure at the center of the end face rotor sleeve 4 corresponds to the hollow structure at the center of the triangular rotor body 1, and end face rotor sleeve sealing grooves 5 matched with the rotor body sealing grooves 2 are formed in three top ends of the end face rotor sleeve 4; specifically, three top department of end face rotor cover 4 all is equipped with two third screw holes 9, two third screw holes 9 are located the both sides rather than the end face rotor cover seal groove 5 that corresponds respectively, all be equipped with on the top surface of triangle rotor body 1 and the bottom surface with third screw hole 9 assorted fourth screw hole 10, third screw hole 9 with also connect through screw 11 between the fourth screw hole 10. Correspond the laminating completely with the top and the bottom of end rotor cover 4 and triangle rotor body 1 and place, use screw 11 in proper order with third screw hole 9 and fourth screw hole 10 fixed connection, end rotor cover 4 adopts wear-resisting material for the friction between terminal surface and the end cover can effectively be dealt with at the during operation to the combination formula rotor in this application, satisfies wear-resisting demand, improves leakproofness and reliability.

Three working face rotor cover 3 and two terminal surface rotor covers 4 are respectively from the outside of triangle rotor body 1, top and bottom with triangle rotor body 1 cover wherein, can change corresponding part after the rotor damages, triangle rotor body 1 can trade the material and subtract heavy to reach rational in infrastructure, make the rotor more durable, improve the thrust-weight ratio of engine, extension engine life.

Furthermore, the center of the working face rotor sleeve 3 is provided with a strip-shaped through hole 12, and the through hole 12 and the triangular rotor body 1 jointly form a working chamber pit, so that the area of a combustion chamber is increased, and the combustion performance is improved.

The utility model discloses a theory of operation: when the utility model is assembled, three working face rotor sleeves 3 are respectively attached and placed on the corresponding outer side faces of the triangular rotor body 1, the first threaded hole 7 and the second threaded hole 8 are fixedly connected through the screw 11, then two end face rotor sleeves 4 are respectively attached and placed at the top and the bottom of the triangular rotor body 1, the end face rotor sleeve sealing groove 5 is placed corresponding to the rotor body sealing groove 2, and the third threaded hole 9 and the fourth threaded hole 10 are fixedly connected through the screw 11; the clearance between working face rotor cover 3 and terminal surface rotor cover 4 is end face seal groove 6, at rotor body seal groove 2 and terminal surface rotor cover seal groove 5 to and the terminal surface seal groove 6 in the installation sealing strip can.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims (4)

1. The utility model provides a combination formula rotor for aerorotor engine, includes three rotor body (1), the three top department of three rotor body (1) all is equipped with rotor body seal groove (2), its characterized in that: three detachable working face rotor sleeves (3) are arranged on the outer side of the triangular rotor body (1), and the three working face rotor sleeves (3) correspond to three side faces of the triangular rotor body (1) mutually; the triangular rotor structure is characterized in that detachable end face rotor sleeves (4) are arranged at the top and the bottom of the triangular rotor body (1), the outer edges of the end face rotor sleeves (4) are triangular structures similar to the outer edge of the triangular rotor body (1) in shape, the centers of the end face rotor sleeves (4) are hollow structures, the hollow structures at the centers of the end face rotor sleeves (4) correspond to the hollow structures at the centers of the triangular rotor body (1), and end face rotor sleeve sealing grooves (5) matched with the rotor body sealing grooves (2) are formed in three top ends of the end face rotor sleeves (4);

and an end face seal groove (6) is formed in a gap between the working face rotor sleeve (3) and the end face rotor sleeve (4).

2. A composite rotor for an aircraft rotor engine, as claimed in claim 1, wherein: every working face rotor cover (3) is close to both ends department and all has seted up first screw hole (7), all seted up on the three side of triangle rotor body (1) with second screw hole (8) corresponding in first screw hole (7), first screw hole (7) with connect through screw (11) between second screw hole (8).

3. A composite rotor for an aircraft rotor engine according to claim 2, characterised in that: three top department of terminal surface rotor cover (4) all is equipped with two third screw holes (9), two third screw hole (9) are located the both sides rather than the terminal surface rotor cover seal groove (5) that corresponds respectively, all be equipped with on the top surface of triangle rotor body (1) and the bottom surface with third screw hole (9) assorted fourth screw hole (10), third screw hole (9) with also connect through screw (11) between fourth screw hole (10).

4. A composite rotor for an aircraft rotor engine, as claimed in claim 1, wherein: the center of the working face rotor sleeve (3) is provided with a strip-shaped through hole (12).

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