CN213331198U

CN213331198U - Turbine disc structure for aircraft engine

Info

Publication number: CN213331198U
Application number: CN202022436886.8U
Authority: CN
Inventors: 于越
Original assignee: Fushun Sanfang Machinery Manufacturing Co ltd
Current assignee: Fushun Sanfang Machinery Manufacturing Co ltd
Priority date: 2020-10-28
Filing date: 2020-10-28
Publication date: 2021-06-01
Anticipated expiration: 2030-10-28

Abstract

The utility model discloses a turbine dish structure for aeroengine belongs to aeroengine accessory technical field, including turbine dish body, the mounting groove has been seted up to turbine dish body periphery, and has seted up the installation breach in the mounting groove outside, installation breach top surface installs the blade, and the blade top is equipped with the connecting plate, the through-hole has been seted up to connecting plate the inner, the fixed lid is installed to the blade top surface, and has seted up the dead slot on the fixed lid top surface, the spring is installed to the inside bottom surface of mounting groove, and the spring top surface is connected with the clamp plate. The utility model discloses in, be connected through setting for the independence blade and turbine dish main part, the blade passes through connecting plate, through-hole, fixed lid, dead slot, mounting groove, spacing section of thick bamboo, fastening device and turbine dish body and constitutes detachable construction for when the individual blade is impaired, can be convenient for change it alone, prevent that the blade and the turbine dish main part of integral type from needing to carry out whole changes to it after impaired, thereby effectively practice thrift the cost.

Description

Turbine disc structure for aircraft engine

Technical Field

The utility model belongs to the technical field of the aeroengine accessory, concretely relates to turbine dish structure for aeroengine.

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 flight of the aircraft, but also an important driving force for promoting the development of aviation industry, each important change in human aviation history is inseparable from the technical progress of the aircraft engine, and a turbine disc is one of important parts of the aircraft engine.

The prior art has the following problems: 1. the existing blades and the turbine disc main body are of an integrated structure and do not have a detachable function, so that all parts are required to be replaced after one group of blades are damaged, and the cost consumption is high; 2. and the function of stably connecting the blades and the turbine disc main body is not provided, so that the blades and the turbine disc main body are easy to loosen.

SUMMERY OF THE UTILITY MODEL

To solve the problems proposed in the background art: 1. the existing blades and the turbine disc main body are of an integrated structure and do not have a detachable function, so that all parts are required to be replaced after one group of blades are damaged, and the cost consumption is high; 2. and do not have the function of stabilizing being connected blade and turbine dish main part for easily produce not hard up problem between it, the utility model provides a turbine dish structure for aeroengine.

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

the utility model provides a turbine dish structure for aeroengine, includes turbine dish body, the mounting groove has been seted up to turbine dish body periphery, and the mounting groove outside has seted up the installation breach, installation breach top surface mounting has the blade, and the blade top is equipped with the connecting plate, the through-hole has been seted up to connecting plate inner, fixed lid is installed to the blade top surface, and fixed lid top surface has seted up the dead slot, the spring is installed to the inside bottom surface of mounting groove, and the spring top surface is connected with the clamp plate, spacing section of thick bamboo is installed to the clamp plate top surface, and spacing section of thick bamboo bottom both ends have seted up spacing mouthful, spacing section of.

Preferably, the fastening mechanism comprises a locking rod, threads are arranged at the upper end of the locking rod, a fastening nut is mounted on the top surface of the locking rod, and a locking plate is fixed at the bottom of the locking rod.

Preferably, the dead slot is big or small cylinder combination column structure, and the dead slot diameter is greater than through-hole diameter, mounting groove diameter, the through-hole diameter is unanimous with lock rod diameter, lock plate width.

Preferably, the blades form a detachable structure with the turbine disc body through the connecting plate, the fixing cover and the fastening mechanism, and the outer end of the fixing cover is flush with the outer end of the turbine disc body.

Preferably, the locking plate is connected with the limiting opening through a pressing plate and a spring, and the height of the limiting opening is consistent with the thickness of the locking plate.

Preferably, the limiting cylinder and the mounting groove form an integrated structure through welding, and the outer diameter of the limiting cylinder is consistent with the diameter of the pressing plate and the diameter of the mounting groove.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the utility model discloses in, be connected through setting for the independence blade and turbine dish main part, the blade passes through connecting plate, through-hole, fixed lid, dead slot, mounting groove, spacing section of thick bamboo, fastening device and turbine dish body and constitutes detachable construction for when the individual blade is impaired, can be convenient for change it alone, prevent that the blade and the turbine dish main part of integral type from needing to carry out whole changes to it after impaired, thereby effectively practice thrift the cost.

2. The utility model discloses in, through setting for fastening device for when pushing down tight lock pole, can make tight lock board act on the clamp plate, the clamp plate makes the spring push down, will lock the rotatory ninety degrees of pole again and coincide with spacing mouthful mutually, the spring resets under the effect of power of no power this moment, clamp plate top surface and spacing section of thick bamboo bottom surface looks butt, again with fastening nut downwardly rotating make its bottom surface until with dead slot lower extreme top surface looks butt, so far can stabilize the blade, fixed lid and turbine disc body and be connected.

3. The utility model discloses in, through setting for fixed lid effect, can be convenient for hide the connection piece on fastening device and the blade, also be convenient for fixed lid is consolidated being connected between blade and the turbine dish, prevents that blade and fastening device from appearing not hard up phenomenon on the turbine dish body when the operation, and fixed lid outer end flushes with this external end of turbine dish for can ensure holistic stability.

Drawings

FIG. 1 is a schematic view of a mid-plane structure of the present invention;

FIG. 2 is a schematic view of a cross-sectional structure of the present invention in a front view;

FIG. 3 is a schematic top view of the fastening mechanism and the limiting cylinder of the present invention;

FIG. 4 is a schematic view of the front structure inside the mounting groove of the present invention;

FIG. 5 is a schematic side view of the middle position-limiting cylinder of the present invention;

fig. 6 is a schematic side view of the fastening mechanism of the present invention.

In the figure: 1. a turbine disk body; 2. a blade; 3. a fixed cover; 4. a fastening mechanism; 401. a locking bar; 402. a thread; 403. fastening a nut; 404. locking the plate; 5. installing a notch; 6. mounting grooves; 7. a spring; 8. pressing a plate; 9. a limiting cylinder; 10. a limiting port; 11. a connecting plate; 12. a through hole; 13. and (4) emptying the groove.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-6, the present invention provides the following technical solutions: a turbine disc structure for an aircraft engine comprises a turbine disc body 1, blades 2, a fixing cover 3, a fastening mechanism 4, a locking rod 401, threads 402, a fastening nut 403, a locking plate 404, an installation notch 5, an installation groove 6, a spring 7, a pressure plate 8, a limiting cylinder 9, a limiting port 10, a connecting plate 11, a through hole 12 and a dead slot 13, wherein the installation groove 6 is formed in the periphery of the turbine disc body 1, the installation notch 5 is formed in the outer side of the installation groove 6, the blades 2 are installed on the top surface of the installation notch 5, the connecting plate 11 is arranged on the top of the blades 2, the through hole 12 is formed in the inner end of the connecting plate 11, the fixing cover 3 is installed on the top surface of the blades 2, the dead slot 13 is formed in the top surface of the fixing cover 3, the spring 7 is installed on the bottom surface inside the installation groove 6, the pressure plate 8 is connected, the limiting cylinder 9 is internally provided with a fastening mechanism 4.

Further, the fastening mechanism 4 is including locking rod 401, and locking rod 401 upper end is equipped with screw thread 402, and fastening nut 403 is installed to locking rod 401 top surface, and locking rod 401 bottom is fixed with locking plate 404, through setting for fastening mechanism 4, can be convenient for stabilize with blade 2, fixed lid 3 and turbine disc body 1 and be connected.

Further, dead slot 13 is big or small cylinder and combines column structure, and dead slot 13 diameter is greater than through-hole 12 diameter, mounting groove 6 diameter, and through-hole 12 diameter is unanimous with lock rod 401 diameter, lock plate 404 width, through setting for dead slot 13, can be convenient for carry on spacing and hide fastening nut 403.

Further, blade 2 passes through connecting plate 11, fixed lid 3, fastening device 4 and turbine dish body 1 constitution detachable construction, and fixed 3 outer ends of lid flush mutually with 1 outer end of turbine dish body, and through setting for it to detachable construction effect, when individual blade 2 is impaired, can be convenient for change alone it, effectively practice thrift the cost.

Further, the locking plate 404 is connected with the limiting opening 10 through the pressing plate 8 and the spring 7, the height of the limiting opening 10 is consistent with the thickness of the locking plate 404, and the locking rod 401 and the limiting barrel 9 can be conveniently connected by setting the limiting opening 10 and the locking plate 404.

Further, a spacing section of thick bamboo 9 constitutes the integral structure through welding and mounting groove 6, and spacing 9 external diameter is unanimous with clamp plate 8 diameter, mounting groove 6 diameter, through setting for spacing section of thick bamboo 9, can be convenient for be connected locking lever 401 and turbine dish body 1, makes locking plate 404 and fastening nut 403 on the locking lever 401 can be connected blade 2, fixed lid 3 and turbine dish body 1 firmly then.

The working principle is as follows: when in use, firstly, the blade 2 and the connecting plate 11 are placed in the installation notch 5 on the turbine disc body 1, then the fixed cover 3 is placed at the top of the connecting plate 11 to be aligned with the turbine disc body 1, then the locking rod 401 of the fastening mechanism 4 sequentially passes through the empty slot 13, the through hole 12 and the installation slot 6 until the locking plate 404 is abutted against the pressure plate 8, then the locking rod 401 is pressed downwards to enable the locking plate 404 to act on the pressure plate 8, the pressure plate 8 enables the spring 7 to be pressed downwards, then the locking rod 401 is rotated ninety degrees until the locking plate 404 is overlapped with the limiting port 10, at the moment, the spring 7 is reset under the condition of no force, the top surface of the pressure plate 8 is abutted against the bottom surface of the limiting cylinder 9, then the fastening nut is rotated downwards to enable the bottom surface to be abutted against the top surface at the lower end of the empty slot 13, so that the blade 2, the fixed cover 3 and the turbine disc body 1 can be stably connected, according to the principle, only the corresponding blade 2 needs to be detached and replaced.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A turbine disk structure for an aircraft engine, comprising a turbine disk body (1), characterized in that: mounting groove (6) have been seted up to turbine dish body (1) periphery, and have seted up installation breach (5) in the mounting groove (6) outside, installation breach (5) top surface mounting has blade (2), and blade (2) top is equipped with connecting plate (11), through-hole (12) have been seted up to connecting plate (11) inner, fixed lid (3) are installed to blade (2) top surface, and just fixed lid (3) top surface has seted up dead slot (13), spring (7) are installed to mounting groove (6) inside bottom surface, and spring (7) top surface is connected with clamp plate (8), spacing section of thick bamboo (9) are installed to clamp plate (8) top surface, and spacing mouthful (10) have been seted up at spacing section of thick bamboo (9) bottom both ends, spacing section of thick bamboo (9) internally mounted has.

2. A turbine disk structure for an aircraft engine according to claim 1, wherein: the fastening mechanism (4) comprises a locking rod (401), threads (402) are arranged at the upper end of the locking rod (401), a fastening nut (403) is installed on the top surface of the locking rod (401), and a locking plate (404) is fixed at the bottom of the locking rod (401).

3. A turbine disk structure for an aircraft engine according to claim 1, wherein: empty groove (13) are big or small cylinder and combine the column structure, and empty groove (13) diameter is greater than through-hole (12) diameter, mounting groove (6) diameter, through-hole (12) diameter is unanimous with locking lever (401) diameter, locking plate (404) width tightly.

4. A turbine disk structure for an aircraft engine according to claim 1, wherein: the blade (2) forms a detachable structure with the turbine disc body (1) through the connecting plate (11), the fixing cover (3) and the fastening mechanism (4), and the outer end of the fixing cover (3) is flush with the outer end of the turbine disc body (1).

5. A turbine disk structure for an aircraft engine according to claim 2, wherein: the locking plate (404) is connected with the limiting opening (10) through the pressing plate (8) and the spring (7), and the height of the limiting opening (10) is consistent with the thickness of the locking plate (404).

6. A turbine disk structure for an aircraft engine according to claim 1, wherein: the limiting cylinder (9) and the mounting groove (6) form an integrated structure through welding, and the outer diameter of the limiting cylinder (9) is consistent with the diameter of the pressing plate (8) and the diameter of the mounting groove (6).