CN220979578U - A turbine blade internal oil cooling structure - Google Patents

Abstract

The utility model discloses an oil cooling structure in a turbine blade, which comprises an oil cooling channel formed in the turbine blade; an oil cooling branch is arranged at the front edge of the turbine blade, and an oil cooling branch is arranged at the tail edge of the turbine blade; the oil cooling branches at the leading edge and the trailing edge of the turbine blade are communicated through a plurality of oil cooling branches at the blade body of the turbine blade to form an oil cooling channel; ports of the oil cooling legs at the leading and trailing edges of the turbine blades are located at the surface of the turbine blades to enable communication with the aircraft oil supply lines. According to the oil cooling structure, the turbine blades are cooled in an oil cooling mode in the blades, and the number and the positions of the oil cooling channels are reasonably arranged according to the distribution condition of a high temperature area, so that the effect of efficiently cooling the blades is achieved. The oil cooling structure has good universality, can improve the problem of fuel to improve the combustion efficiency while cooling the blades, and has double functions.

Description

A turbine blade internal oil cooling structure

Technical Field

The utility model relates to the technical field of aviation engines, in particular to an internal oil cooling structure of a turbine blade.

Background technique

As the temperature before the turbine increases year by year, the material can no longer meet the temperature resistance requirements, and a cooling structure is needed to cool the material. At present, the cooling method mainly used is air cooling, that is, drawing cold air from the compressor to cool the high-temperature components. Since air cooling requires drawing cold air flow from the compressor, it directly causes a reduction in mainstream flow, which will affect the combustion efficiency of the engine and reduce the sharpness of the engine. In addition, the traditional aviation gas turbine engine is in an expansion and cooling process in the turbine channel, and the heat load of the blade body is lower than the leading edge of the turbine. This is completely opposite to the heat load distribution on the blade surface after combustion in the inter-blade channel. The air film cooling of the blade body will further promote the secondary combustion reaction of the inter-blade channel, causing the cooling problem of the turbine blade. Based on this, the air cooling method in the prior art has various disadvantages.

Therefore, based on the above technical problems, technicians in this field urgently need to develop an internal oil cooling structure for turbine blades.

Utility Model Content

The utility model aims to provide an internal oil cooling structure for turbine blades which uses the engine's own fuel for oil cooling, and the cooled high-temperature fuel is then burned, thereby cooling the high-temperature components and increasing the combustion temperature of the fuel to improve the combustion efficiency.

In order to achieve the above purpose, the utility model provides the following technical solutions:

The utility model discloses an internal oil cooling structure for a turbine blade, wherein the oil cooling structure is formed inside the turbine blade and comprises:

an oil cooling passage formed inside the turbine blade, the oil cooling passage being in communication with an oil supply line of the aircraft so as to introduce fuel into the oil cooling passage and to exchange heat with the turbine blade;

An oil cooling branch is provided at the leading edge of the turbine blade, and an oil cooling branch is provided at the trailing edge of the turbine blade;

The oil cooling branches at the leading edge and the trailing edge of the turbine blade are connected through a plurality of oil cooling branches at the blade body of the turbine blade to form an oil cooling channel;

The ports of the oil cooling branches at the leading edge and the trailing edge of the turbine blade are located on the surface of the turbine blade to achieve communication with the oil supply pipeline of the aircraft.

Furthermore, at least two oil cooling branches are arranged at a position of the blade body of the turbine blade close to the leading edge of the turbine blade;

At least two oil cooling branches are arranged on the blade body of the turbine blade near the trailing edge of the turbine blade;

The distance between the oil cooling branches near the leading edge of the turbine blade is smaller than the distance between the oil cooling branches near the trailing edge.

Furthermore, the oil cooling branch adopts a vertical square tube extending along the thickness direction of the turbine blade, and the interior of the vertical square tube is hollow to form a fuel channel;

Adjacent oil cooling branches are connected to internal fuel channels via connecting channels.

Further, the communication channel is configured as a circular channel disposed inside the turbine blade;

The circular channel matches the opening size of the fuel channel of the oil cooling branch, and the fuel channels of adjacent oil cooling branches are connected through the circular channel.

Furthermore, the plurality of oil cooling branches are connected through the corresponding connecting passages to form an oil cooling passage extending in a bent shape in the turbine blade.

Furthermore, the cross-sectional dimensions of the oil cooling channel at the trailing edge of the turbine blade are smaller than the cross-sectional dimensions of the oil cooling channel at other positions.

In the above technical solution, the utility model provides a turbine blade internal oil cooling structure, which has the following beneficial effects:

The oil cooling structure of the utility model cools the turbine blades by means of oil cooling inside the blades, and reasonably arranges the number and position of the oil cooling channels according to the distribution of the high temperature area to achieve the effect of efficiently cooling the blades. The oil cooling structure has good versatility, and can improve the fuel problem to improve the combustion efficiency while cooling the blades, and has a dual role.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present utility model. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

FIG1 is a schematic structural diagram of an internal oil cooling structure of a turbine blade provided by an embodiment of the utility model;

FIG2 is a schematic structural diagram of an internal oil cooling channel of an internal oil cooling structure of a turbine blade provided by an embodiment of the utility model;

FIG3 is a cross-sectional view of an internal oil cooling structure of a turbine blade provided in an embodiment of the utility model.

Description of reference numerals:

10. Turbine blades; 20. Oil cooling channel;

11. Leading edge; 12. Trailing edge; 13. Blade body;

21. Oil cooling branch; 22. Connecting channel.

Detailed ways

In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below in conjunction with the accompanying drawings.

See Figures 1 to 3;

This embodiment discloses an oil cooling structure inside a turbine blade. The oil cooling structure is formed inside a turbine blade 10 and includes:

An oil cooling passage 20 is formed inside the turbine blade 10 , and the oil cooling passage 20 is connected to the oil supply pipeline of the aircraft so that the fuel is introduced into the oil cooling passage 20 and heat-exchanged with the turbine blade 10 ;

An oil cooling branch 21 is provided at the leading edge 11 of the turbine blade 10 , and an oil cooling branch 21 is provided at the trailing edge 12 of the turbine blade 10 ;

The oil cooling branches 21 at the leading edge 11 and the trailing edge 12 of the turbine blade 10 are connected through a plurality of oil cooling branches 21 at the blade body 13 of the turbine blade 10 to form an oil cooling channel 20;

The ports of the oil cooling branches 21 at the leading edge 11 and the trailing edge 12 of the turbine blade 10 are located on the surface of the turbine blade 10 to achieve communication with the oil supply pipeline of the aircraft.

Specifically, the present embodiment discloses a novel oil-cooling structure inside a turbine blade 10, which first arranges an oil-cooling branch 21 at the leading edge 11 and the trailing edge 12 of the turbine blade 10, and arranges a plurality of oil-cooling branches 21 on the blade body 13 according to the distribution of the high-temperature area of the blade body 13. The plurality of oil-cooling branches 21 of the present embodiment are connected to each other to form an oil-cooling channel 20 connected to the aircraft fuel supply pipeline. The low-temperature cold oil is transported to the turbine blade 10 through the oil-cooling channel 20 to exchange heat with the turbine blade 10, and can take away the temperature of the turbine blade 10 and increase the temperature of the fuel. The high-temperature fuel then refluxes to perform the combustion function, thereby not only being able to cool the turbine blade 10 by oil cooling, but also being able to improve the fuel problem to improve the combustion efficiency.

Preferably, at least two oil cooling branches 21 are arranged at a position of the blade body 13 of the turbine blade 10 of this embodiment close to the leading edge 11 of the turbine blade 10;

At least two oil cooling branches 21 are arranged at a position of the blade body 13 of the turbine blade 10 close to the trailing edge 12 of the turbine blade 10;

The distance between the oil cooling branches 21 near the leading edge 11 of the blade body 13 of the turbine blade 10 is smaller than the distance between the oil cooling branches 21 near the trailing edge 12 .

In this embodiment, multiple oil cooling branches 21 are arranged inside the turbine blade 10, and the fuel oil is subsequently burned after heat exchange with the blade through the oil circuit. The geometric model is a C3X blade, and an oil cooling branch 21 is arranged near the leading edge 11 and the trailing edge 12. The oil cooling branch 21 is arranged in the blade body 13 area according to the distribution of the high temperature zone. Considering the oxidation and coking problem of the fuel oil in the channel, the cooling structure is evaluated as a whole before designing. The temperature rise of the fuel oil in the entire oil cooling channel 20 conforms to the fluid heat balance equation. The design is carried out by using the convection heat transfer correlation, heat transfer equation, fluid heat balance equation, etc. to make a preliminary temperature estimate, and after preliminary calculation through a one-dimensional empirical relationship, it is improved by using three-dimensional simulation. Finally, an even number of oil cooling branches are arranged (this application takes 6 oil cooling branches as an example for further explanation and description), which can realize the fuel oil entering and exiting from a single direction.

Preferably, the oil cooling branch 21 of this embodiment adopts a vertical square tube extending along the thickness direction of the turbine blade 10, and the interior of the vertical square tube is hollow to form a fuel channel;

Adjacent oil cooling branches 21 are connected to internal fuel channels via connecting channels 22 .

In order to reduce the stress at the connection, the communication channel 22 of this embodiment is configured as a circular channel disposed inside the turbine blade 10;

The circular channel matches the opening size of the fuel channel of the oil cooling branch 21, and the fuel channels of adjacent oil cooling branches are connected through the circular channel.

Six oil cooling branches 21 are arranged inside the turbine blade 10 of this embodiment, and vertical square tubes are used as the oil cooling branches 21 arranged inside the turbine blade 10, and adjacent oil cooling branches 21 are connected to multiple fuel channels through circular channels, that is, the above-mentioned connecting channels 22 to form a whole oil cooling channel 20. The cross-sectional area of the oil cooling branch 21 can be adjusted according to the actual situation of the blade, so as to realize flexible design and adjustment of the cooling structure inside the blade, and has good versatility.

A one-dimensional empirical relationship is used to calculate the temperature rise of the fuel at a given flow rate, and the fuel outlet temperature is controlled below the coking temperature to prevent the fuel from cracking and coking in the oil circuit, thereby blocking the oil circuit.

In this embodiment, the plurality of oil cooling branches are formed into an oil cooling channel extending in a bent shape in the turbine blade through corresponding connecting passages.

Preferably, the cross-sectional dimensions of the oil cooling channel 20 at the trailing edge 12 of the turbine blade 10 of this embodiment are smaller than the cross-sectional dimensions of the oil cooling channel 20 at other positions. Due to the thickness of the blade at the trailing edge 12, the cross-sectional area of the oil cooling branch 21 needs to be reduced accordingly, and it has the same cross-sectional dimensions as the five oil cooling branches 21 and is arranged in parallel. The channels are connected by circular channels to reduce stress, and the cross-sectional dimensions of the circular channels at the trailing edge 12 also need to be reduced accordingly.

In the above technical solution, the utility model provides a turbine blade internal oil cooling structure, which has the following beneficial effects:

The oil cooling structure of the utility model cools the turbine blade 10 by means of oil cooling inside the blade, and reasonably arranges the number and position of the oil cooling channel 20 according to the distribution of the high temperature area to achieve the effect of efficiently cooling the blade. The oil cooling structure has good versatility, and can improve the problem of fuel to improve the combustion efficiency while cooling the blade, and has a dual role.

The above only describes some exemplary embodiments of the present invention by way of illustration. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims (2)

1. A turbine blade internal oil cooling structure, characterized in that the oil cooling structure is formed inside the turbine blade (10), and comprises: An oil cooling passage (20) is formed inside the turbine blade (10), the oil cooling passage (20) being in communication with an oil supply pipeline of the aircraft so that fuel can be introduced into the oil cooling passage (20) and exchange heat with the turbine blade (10); An oil cooling branch (21) is provided at the leading edge (11) of the turbine blade (10), and an oil cooling branch (21) is provided at the trailing edge (12) of the turbine blade (10); The oil cooling branches (21) at the leading edge (11) and the trailing edge (12) of the turbine blade (10) are connected through a plurality of oil cooling branches (21) at the blade body (13) of the turbine blade (10) to form an oil cooling channel (20); The ports of the oil cooling branch (21) at the leading edge (11) and the trailing edge (12) of the turbine blade (10) are located on the surface of the turbine blade (10) so as to be connected with the oil supply pipeline of the aircraft; At least two oil cooling branches (21) are arranged on the blade body (13) of the turbine blade (10) near the leading edge (11) of the turbine blade (10); At least two oil cooling branches (21) are arranged on the blade body (13) of the turbine blade (10) near the trailing edge (12) of the turbine blade (10); The distance between the oil cooling branches (21) of the blade body (13) of the turbine blade (10) near the leading edge (11) is smaller than the distance between the oil cooling branches (21) near the trailing edge (12); The oil cooling branch (21) is a vertical square tube extending in the thickness direction of the turbine blade (10), and the interior of the vertical square tube is hollow to form a fuel channel; Adjacent oil cooling branches (21) are connected to internal fuel channels via a connecting channel (22); The communication channel (22) is configured as a circular channel arranged inside the turbine blade (10); The circular channel matches the opening size of the fuel channel of the oil cooling branch (21), and the fuel channels of adjacent oil cooling branches (21) are connected through the circular channel; The cross-sectional dimensions of the oil cooling channel (20) at the trailing edge (12) of the turbine blade (10) are smaller than the cross-sectional dimensions of the oil cooling channel (20) at other locations. 2. An internal oil cooling structure for a turbine blade according to claim 1, characterized in that a plurality of the oil cooling branches (21) are connected through corresponding connecting passages (22) to form an oil cooling passage (20) extending in a bent shape inside the turbine blade (10).