CN209818116U

CN209818116U - Turbine rotor blade with axial protrusions

Info

Publication number: CN209818116U
Application number: CN201920530653.9U
Authority: CN
Inventors: 庄来杰; 艾厚望; 万媛媛; 杨养花; 马增祥
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2019-04-18
Filing date: 2019-04-18
Publication date: 2019-12-20
Anticipated expiration: 2029-04-18

Abstract

The present application relates to a turbine rotor blade with axial bulge, the turbine rotor blade has a blade body, the tip of blade body has the tip shroud, at least, have a peripheral extension and protrusion on the tip shroud the comb tooth on tip shroud surface, at least, have a arch that extends along the axis direction on the comb tooth. According to the turbine rotor blade with the axial protrusions, in the axial moving process of the rotor and the stator, the protrusions on the grid teeth can be in contact with the honeycomb before the linear parts on the grid teeth, so that the honeycomb is ground, the open-circuit effect is achieved, the linear parts of the grid teeth are prevented from being in collision with the honeycomb, and the axial acting force brought to the rotor blade by the grid teeth and the honeycomb collision can be effectively reduced by changing the abrasion form of the grid teeth and the honeycomb. Under the condition of having little influence on the weight of the rotor blade, the axial acting force brought to the rotor blade when the turbine rotor and the stator are rubbed and ground is greatly reduced, and the reliability and the safety of the engine are improved.

Description

Turbine rotor blade with axial protrusions

Technical Field

The application belongs to the technical field of aeroengines, and particularly relates to a turbine rotor blade with axial protrusions.

Background

As shown in FIGS. 1 and 2, the blade body 11 of the low-pressure turbine rotor blade 1 is generally provided with a tip shroud 12 at the end, and the tip shroud 12 is provided with a comb tooth 13. The grate 13 is mainly used for reducing vibration and ensuring turbine efficiency. In the conventional design of the comb tooth 13 of the blade crown 12, two straight lines arranged in parallel in the front and back direction are generally adopted to form the comb tooth 13, and the comb tooth 13 is matched with a honeycomb 22 arranged on a stator casing 21 fixed on the stator member 2. The low-pressure turbine rotor blade 1 is twisted through the blade pre-twisting angle and assembly, so that the whole circle of blades are connected into a whole, and the honeycomb 21 with low hardness is matched with the blades, so that the aim of shock absorption can be achieved, and the working efficiency of the low-pressure turbine can be ensured.

However, in the engine operation, the relative positions of the rotor and the stator in the radial direction and the circumferential direction are changed, and the changing direction is not fixed. As shown in fig. 3, in an ideal state, there should be a certain gap between the comb 13 of the rotor blade 1 and the honeycomb 22 of the stator casing 21. However, during operation, the rotor and the stator are subjected to radial rubbing and are accompanied with axial and radial play, so that the comb teeth 13 on the blade crown 12 are clamped into the honeycomb 22, as shown in fig. 4, the honeycomb 22 is correspondingly subjected to loss in both axial and radial directions, axial acting force is brought to the rotor, and the use safety and reliability of the engine are damaged.

Disclosure of Invention

It is an object of the present application to provide a turbine rotor blade with an axial projection to address at least one problem in the prior art.

The technical scheme of the application is as follows: a turbine rotor blade with an axial projection, the turbine rotor blade having a blade body, a blade shroud at the end of the blade body, the blade shroud having at least one circumferentially extending tooth projecting from the surface of the blade shroud, the tooth having at least one projection extending in the axial direction.

In this application, the shape of the protrusion includes one of a triangle or a trapezoid.

In the present application, the protrusions are located at the end portions of the grate in the axial direction.

According to the turbine rotor blade with the axial protrusions, in the axial moving process of the rotor and the stator, the protrusions on the grid teeth can be in contact with the honeycomb before the linear parts on the grid teeth, so that the honeycomb is ground, the open-circuit effect is achieved, the linear parts of the grid teeth are prevented from being in collision with the honeycomb, and the axial acting force brought to the rotor blade by the grid teeth and the honeycomb collision can be effectively reduced by changing the abrasion form of the grid teeth and the honeycomb. Under the condition of having little influence on the weight of the rotor blade, the axial acting force brought to the rotor blade when the turbine rotor and the stator are rubbed and ground is greatly reduced, and the reliability and the safety of the engine are improved.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a schematic view of a prior art rotor blade.

Fig. 2 is a schematic view of a prior art stator member.

FIG. 3 is a schematic view of a prior art rotor blade and stator assembly in an assembled state.

FIG. 4 is a schematic view of a prior art transition state of a rotor blade and a stator member.

FIG. 5 is a schematic view of a rotor blade of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

Compared with the honeycombs of the low-pressure turbine rotor blade and the stator part in the prior art, the axial float can occur when the rotor and the stator are radially rubbed and abraded in some states in the working engineering. Under the condition, because the comb teeth of the blade crown can be clamped in the honeycomb, the axial movement can bring extra and uncontrolled axial acting force to the rotor blade, and the working efficiency of the low-pressure turbine and the reliability of the engine are influenced. Therefore, the turbine rotor blade with the axial protrusions reduces the axial acting force caused by collision and abrasion of the rotor and the stator in the axial moving process of the rotor and the stator, and improves the reliability and the safety of an engine.

The turbine rotor blade with the axial protrusions comprises a blade body, a blade shroud is arranged at the end of the blade body in the radial Y direction, at least one comb tooth extending in the circumferential C direction is arranged on the blade shroud, the surface of the blade shroud protrudes in the radial direction, and at least one protrusion extending in the axial X direction is arranged on the comb tooth.

In the present application, the cross-sectional shape of the protrusion may be triangular, semi-triangular, trapezoidal, and other shapes. The protrusions act as "open-circuit pioneers" of the comb in the axial direction, i.e. contacting and rubbing against the honeycomb beforehand, and for better grinding of the grooves in the honeycomb, the protrusions are therefore preferably sharply pointed at the ends, i.e. triangular.

In the present application, the position of the protrusion is not limited to any position of the grate, but is preferably set at the starting position, i.e., the starting position in the circumferential direction of the rotation of the circumferential vanes.

As shown in fig. 5, according to an embodiment of the present invention, in the embodiment, two comb teeth 33 are provided on the blade body 31 of the turbine rotor blade 3, the comb teeth 33 are arranged in parallel, a certain interval is provided between the two comb teeth 33, each comb tooth 33 has only one protrusion 34, and the protrusions 34 on the two comb teeth 33 are centrosymmetric with the radial axis of the blade body 31. The projections 34 are triangular in shape.

In the above embodiment, the number of the grid teeth 33 may be one or more. The number of the protrusions 34 on the single grate 33 may be two or more.

It should be noted that the volume of the protrusion 34 in the present application is not too large to increase the weight of the rotor blade.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A turbine rotor blade with axial protrusions is characterized in that the turbine rotor blade (3) is provided with a blade body (31), a blade shroud (32) is arranged at the end part of the blade body (31), at least one grate tooth (33) which extends in the circumferential direction and protrudes out of the surface of the blade shroud (32) is arranged on the blade shroud (32), and at least one protrusion (34) which extends in the axial direction is arranged on the grate tooth (33).

2. The turbine rotor blade according to claim 1, wherein the shape of the protrusion (34) comprises one of a triangle or a trapezoid.

3. The turbine rotor blade according to claim 1 or 2, characterized in that the protrusion (34) is located at the end of the grate (33) in the axial direction.