CN215057588U

CN215057588U - Aeroengine rotor blade with inclined tenon structure

Info

Publication number: CN215057588U
Application number: CN202121267833.6U
Authority: CN
Inventors: 田杰; 何飞飞; 谢伟; 袁增宝
Original assignee: Xi'an Zhongjiefei Industry And Trade Co ltd
Current assignee: Xi'an Zhongjiefei Industry And Trade Co ltd
Priority date: 2021-06-07
Filing date: 2021-06-07
Publication date: 2021-12-07
Anticipated expiration: 2031-06-07

Abstract

The utility model discloses an aeroengine rotor blade of oblique tenon structure, including the blade base, the riveting has engine blade on the blade base, blade base intermediate position has been seted up and has been seted up mounting groove, install the fan cone in the mounting groove, engine blade edge installs heat dissipation mechanism, heat dissipation mechanism includes mechanism's shell, heat dissipation recess, heat dissipation copper pipe, pipeline cavity, first opening and second opening, be connected with extrinsic cycle mechanism on the heat dissipation copper pipe, extrinsic cycle mechanism is including heat dissipation pipeline, connecting tube, water pump, first interface and second interface, mechanism's shell is installed in engine blade edge, mechanism's shell inboard is equipped with heat dissipation recess, be equipped with the pipeline cavity in the mechanism's shell, fixed mounting has heat dissipation copper pipe in the pipeline cavity. An aeroengine rotor blade of oblique tenon structure, belong to the engine blade field, can give the blade cooling fast.

Description

Aeroengine rotor blade with inclined tenon structure

Technical Field

The utility model relates to an engine blade field, in particular to aeroengine rotor blade of oblique tenon head structure.

Background

The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine. The aero-engine has been developed into a mature product with extremely high reliability, and the aero-engine in use includes various types such as a turbojet/turbofan engine, a turboshaft/turboprop engine, a ramjet engine and a piston engine, and not only is used as power for military and civil aircrafts, unmanned planes and cruise missiles for various purposes, but also a gas turbine developed by derivation of the aero-engine is widely used in the fields of ground power generation, marine power, mobile power stations, natural gas and petroleum pipeline pumping stations and the like. The engine rotor blades are typically mounted to the blade mounts by riveting. The linear velocity of engine rotor blade at high-speed rotatory in-process blade edge is very big, and the terminal temperature of blade that rubs with the air can be very high in the high-speed rotatory in-process of blade, if can not let in time dispel the heat can influence the life of blade.

SUMMERY OF THE UTILITY MODEL

The utility model discloses a main aim at provides an aeroengine rotor blade of oblique tenon head structure can effectively solve the problem of mentioning in the background art.

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

the utility model provides an aeroengine rotor blade of oblique tenon structure, includes the blade base, the riveting has engine blade on the blade base, mounting groove has been seted up to blade base intermediate position, install the fan cone in the mounting groove, engine blade edge installs heat dissipation mechanism, heat dissipation mechanism includes mechanism's shell, heat dissipation recess, heat dissipation copper pipe, pipeline cavity, first opening and second opening, be connected with extrinsic cycle mechanism on the heat dissipation copper pipe, extrinsic cycle mechanism includes heat dissipation pipeline, connecting tube, water pump, first interface and second interface.

Preferably, the mechanism shell is installed at the edge of the engine blade, a heat dissipation groove is formed in the inner side of the mechanism shell, a pipeline cavity is formed in the mechanism shell, a heat dissipation copper pipe is fixedly installed in the pipeline cavity, a first opening is formed in the mechanism shell, and a second opening is formed in one side, located on the first opening, of the mechanism shell.

Preferably, the heat dissipation copper pipe is installed in the mechanism shell through a pipeline cavity, one end of the heat dissipation copper pipe extends out of the pipeline cavity through a first opening, the other end of the heat dissipation copper pipe extends out of the pipeline cavity through a second opening, and the tail end of the engine blade is limited to rotate in the heat dissipation groove.

Preferably, the connecting pipeline is connected to the heat dissipation copper pipe, a water pump is fixedly mounted at the tail end of the connecting pipeline, a first connector is fixedly mounted on one side of the water pump, a second connector is fixedly mounted on the other side of the water pump, and the heat dissipation pipeline is connected to the second connector.

Preferably, one end of the heat dissipation pipeline is connected to the water pump through a second interface, the other end of the heat dissipation pipeline is connected to one end of the heat dissipation copper pipe, one end of the connecting pipeline is connected to the water pump through a first interface, and the other end of the connecting pipeline is connected to the other end of the heat dissipation copper pipe.

Preferably, the wind cone is installed on the blade base through an installation groove, an inclined tenon is arranged on the blade base, and the engine blade is riveted on the blade base through the inclined tenon.

Compared with the prior art, the utility model discloses following beneficial effect has:

the utility model discloses in, the coolant liquid can flow fast in the pipeline after the start-up water pump, and the coolant liquid can absorb the heat that the engine blade end produced after the coolant liquid flows heat dissipation copper pipe department to give the engine blade cooling fast, the coolant liquid can dispel the heat to the outside after the coolant liquid flows heat dissipation pipeline department, thereby cooling for the coolant liquid.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

fig. 2 is a schematic view of the heat dissipation structure of the present invention;

fig. 3 is a schematic view of the external circulation mechanism of the present invention.

In the figure: 1. a heat dissipation mechanism; 101. a mechanism housing; 102. a heat dissipation groove; 103. a heat dissipation copper pipe; 104. a pipe cavity; 105. a first gap; 106. a second gap; 2. an engine blade; 3. a blade base; 4. a wind cone; 5. installing a groove; 6. an external circulation mechanism; 601. a heat dissipation pipe; 602. connecting a pipeline; 603. a water pump; 604. a first interface; 605. a second interface.

Detailed Description

In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.

As shown in fig. 1-3, an aircraft engine rotor blade with an oblique tenon structure comprises a blade base 3, an engine blade 2 is riveted on the blade base 3, a mounting groove 5 is formed in the middle of the blade base 3, a wind cone 4 is mounted in the mounting groove 5, a heat dissipation mechanism 1 is mounted at the edge of the engine blade 2, the heat dissipation mechanism 1 comprises a mechanism shell 101, a heat dissipation groove 102, a heat dissipation copper pipe 103, a pipeline cavity 104, a first opening 105 and a second opening 106, an outer circulation mechanism 6 is connected to the heat dissipation copper pipe 103, the outer circulation mechanism 6 comprises a heat dissipation pipeline 601, a connecting pipeline 602, a water pump 603, a first interface 604 and a second interface 605, the wind cone 4 is mounted on the blade base 3 through the mounting groove 5, an oblique tenon is arranged on the blade base 3, and the engine blade 2 is riveted on the blade base 3 through the oblique tenon.

In this embodiment, in order to dissipate heat for the engine blade 2, the heat dissipating mechanism 1 is installed at the edge of the engine blade 2, the heat dissipating mechanism 1 includes a mechanism casing 101, a heat dissipating groove 102, a heat dissipating copper pipe 103, a pipe cavity 104, a first opening 105 and a second opening 106, an outer circulation mechanism 6 is connected to the heat dissipating copper pipe 103, the outer circulation mechanism 6 includes a heat dissipating pipe 601, a connecting pipe 602, a water pump 603, a first interface 604 and a second interface 605, the mechanism casing 101 is installed at the edge of the engine blade 2, the heat dissipating groove 102 is installed at the inner side of the mechanism casing 101, the pipe cavity 104 is installed in the mechanism casing 101, the heat dissipating copper pipe 103 is fixedly installed in the pipe cavity 104, the first opening 105 is opened on the mechanism casing 101, the second opening 106 is opened at one side of the first opening 105 on the mechanism casing 101, the heat dissipating copper pipe 103 is installed in the mechanism casing 101 through the pipe cavity 104, one end of the heat dissipating copper pipe 103 extends out of the pipe cavity 104 through the first opening 105, the other end of the heat dissipation copper pipe 103 extends out of the pipe cavity 104 through the second notch 106, the tail end of the engine blade 2 is limited to rotate in the heat dissipation groove 102, the connecting pipe 602 is connected to the heat dissipation copper pipe 103, the tail end of the connecting pipe 602 is fixedly provided with the water pump 603, one side of the water pump 603 is fixedly provided with the first interface 604, the other side of the water pump 603 is fixedly provided with the second interface 605, the second interface 605 is connected with the heat dissipation pipe 601, one end of the heat dissipation pipe 601 is connected to the water pump 603 through the second interface 605, the other end of the heat dissipation pipe 601 is connected to one end of the heat dissipation copper pipe 103, one end of the connecting pipe 602 is connected to the water pump 603 through the first interface 604, the other end of the connecting pipe 602 is connected to the other end of the heat dissipation copper pipe 103, the cooling liquid can rapidly flow in the pipe after the water pump 603 is started, the cooling liquid can absorb heat generated by the tail end of the engine blade 2 after the cooling liquid flows to the heat dissipation copper pipe 103, thereby fast for engine blade 2 cooling, the coolant liquid can dispel the heat to the outside after the coolant liquid flows to heat dissipation pipeline 601 department to for the coolant liquid cooling, circulate in proper order just can be in real time for engine blade 2 heat dissipation.

It should be noted that, the utility model relates to an aeroengine rotor blade of oblique tenon structure, in the time of practical use, at first install heat dissipation mechanism 1 in 2 edges of engine blade, install outside the engine with heat dissipation pipeline 601 simultaneously, later start-up water pump 603, the coolant liquid will be at the pipeline internal circulation flow after start-up water pump 603, the coolant liquid flows the heat that the back coolant liquid of heat dissipation copper pipe 103 department can absorb 2 terminal productions of engine blade, thereby give engine blade 2 cooling fast, the coolant liquid flows the back coolant liquid of heat dissipation pipeline 601 department and can dispel the heat to the outside, thereby for the coolant liquid cooling, the in-process of circulation flow just can be fast for engine blade 2 heat dissipation, thereby improve engine blade 2's life.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides an aeroengine rotor blade of tenon structure which characterized in that: including blade base (3), engine blade (2) have been riveted on blade base (3), mounting groove (5) have been seted up to blade base (3) intermediate position, install fan cone (4) in mounting groove (5), heat dissipation mechanism (1) is installed to engine blade (2) edge, heat dissipation mechanism (1) is including mechanism shell (101), heat dissipation groove (102), heat dissipation copper pipe (103), pipeline cavity (104), first opening (105) and second opening (106), be connected with extrinsic cycle mechanism (6) on heat dissipation copper pipe (103), extrinsic cycle mechanism (6) are including heat dissipation pipeline (601), connecting tube (602), water pump (603), first interface (604) and second interface (605).

2. An aircraft engine rotor blade of skewed tenon construction as defined in claim 1, wherein: the mechanism comprises a mechanism shell (101), a heat dissipation groove (102) is formed in the inner side of the mechanism shell (101), a pipeline cavity (104) is arranged in the mechanism shell (101), a heat dissipation copper pipe (103) is fixedly mounted in the pipeline cavity (104), a first opening (105) is formed in the mechanism shell (101), and a second opening (106) is formed in one side, located on the first opening (105), of the mechanism shell (101).

3. An aircraft engine rotor blade of skewed tenon construction as defined in claim 2, wherein: the heat dissipation copper pipe (103) is installed in the mechanism shell (101) through a pipe cavity (104), one end of the heat dissipation copper pipe (103) extends out of the pipe cavity (104) through a first opening (105), the other end of the heat dissipation copper pipe (103) extends out of the pipe cavity (104) through a second opening (106), and the tail end of the engine blade (2) is limited to rotate in the heat dissipation groove (102).

4. An aircraft engine rotor blade of the rebate configuration of claim 3, wherein: the connecting pipe (602) is connected to the heat dissipation copper pipe (103), a water pump (603) is fixedly mounted at the tail end of the connecting pipe (602), a first connector (604) is fixedly mounted on one side of the water pump (603), a second connector (605) is fixedly mounted on the other side of the water pump (603), and the heat dissipation pipe (601) is connected to the second connector (605).

5. An aircraft engine rotor blade of the rebate configuration of claim 4, wherein: one end of the heat dissipation pipeline (601) is connected to the water pump (603) through a second interface (605), the other end of the heat dissipation pipeline (601) is connected to one end of the heat dissipation copper pipe (103), one end of the connecting pipeline (602) is connected to the water pump (603) through a first interface (604), and the other end of the connecting pipeline (602) is connected to the other end of the heat dissipation copper pipe (103).

6. An aircraft engine rotor blade of skewed tenon construction as defined in claim 5, wherein: the fan cone (4) is installed on the blade base (3) through the installation groove (5), an inclined tenon is arranged on the blade base (3), and the engine blade (2) is riveted on the blade base (3) through the inclined tenon.