CN213450508U

CN213450508U - High-pressure rotor for gas turbine and air duct thereof

Info

Publication number: CN213450508U
Application number: CN202022439768.2U
Authority: CN
Inventors: 王家广; 江奔; 陆晓锋
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-10-28
Filing date: 2020-10-28
Publication date: 2021-06-15
Anticipated expiration: 2030-10-28

Abstract

The air conduit for the high-pressure rotor of the gas turbine has strong heat insulation capability and good vibration resistance, and comprises an outer layer, an inner layer, an intermediate layer and a heat insulation material; the inner layer extends within the outer layer; the middle layer is arranged between the outer layer and the inner layer; the middle layer comprises two layers, the transverse section of each layer comprises fixing parts and non-fixing parts which are alternately arranged along the circumferential direction, one non-fixing part positioned on the opposite outer circumferential side in the two layers is opposite to and in surface contact with the other non-fixing part positioned on the opposite inner circumferential side, the one fixing part and the other fixing part are opposite to each other to form a cavity, the one fixing part is connected and fixed with the outer layer, the cavity is formed between the non-fixing part and the outer layer, the other fixing part is connected and fixed with the inner layer, and the cavity is formed between the one non-fixing part and the outer layer. An insulating material is filled in each cavity.

Description

High-pressure rotor for gas turbine and air duct thereof

Technical Field

The utility model relates to a high-pressure rotor for gas turbine and air conduit thereof.

Background

In the prior aeroengine, an air conduit for forming an independent air cavity is usually arranged on an inner cavity of a high-pressure rotor, as shown in fig. 1, an air conduit 5 is arranged on a blade disc 1 of a compressor and a rear shaft 4 of a high-pressure turbine, and the air conduit, the sealing disc 2 and a turbine disc 3 form the inner cavity of the rotor. The air duct 5 is used to convey air in the high-pressure rotor passage to the high-pressure turbine, cooling the rotor of the high-pressure turbine.

The inventors found that the air duct has the following problems:

1) the heat insulation effect of the current air guide pipe needs to be improved, other cooling gas in the inner cavity of the rotor and a fan shaft penetrating through the inner cavity of the rotor can be heated, and the risk of over-temperature of the fan shaft and a high-temperature component at the rear end is caused;

2) the current air conduit has great slenderness ratio because bleed air route is longer and space restriction, under the effect of air current exciting force and self unbalance amount, air conduit very easily takes place the vibration at the during operation, takes place the flutter even, and then has the risk of damaging air conduit.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an air conduit for high-pressure rotor of gas turbine, it has the anti vibration ability of preferred when having stronger thermal-insulated ability.

It is another object of the present invention to provide a high pressure rotor for a gas turbine.

An air duct for a high-pressure rotor of a gas turbine includes an outer layer, an inner layer, an intermediate layer, and a heat insulating material; an inner layer extending within the outer layer; an intermediate layer disposed between the outer layer and the inner layer; the middle layer comprises two layers, the transverse section of each layer comprises fixing parts and non-fixing parts which are alternately arranged along the circumferential direction, one non-fixing part positioned on the opposite outer circumferential side in the two layers is opposite to and in surface contact with the other non-fixing part positioned on the opposite inner circumferential side, the one fixing part and the other fixing part are opposite to each other to form a cavity, the one fixing part is fixedly connected with the outer layer, the cavity is formed between the non-fixing part and the outer layer, the other fixing part is fixedly connected with the inner layer, and the cavity is formed between the non-fixing part and the outer layer. The heat insulating material is filled in the cavity.

In one embodiment, each of the intermediate layers has a wavy transverse cross section, wherein one of the valleys of each of the two layers on the outer peripheral side is in surface contact with the other of the valleys of each of the two layers on the inner peripheral side, the one of the valleys and the other of the valleys form a cavity facing each other, the one of the peaks is fixedly connected to the outer layer, the one of the valleys and the outer layer form a cavity therebetween, the other of the valleys and the inner layer are fixedly connected to the inner layer, and a cavity is formed between the one of the peaks and the outer layer.

In one embodiment, the connection is fixed as a weld.

In one embodiment, the material of the outer layer, the inner layer, the intermediate layer is selected from a titanium alloy or a superalloy.

In one embodiment, the insulating material is selected from polyurethane foam or phenolic foam.

In one embodiment, the outer layer and the inner layer are welded directly to one piece at both ends of the air duct.

The high-pressure rotor of the gas turbine comprises a high-pressure compressor rotor, a high-pressure turbine rotor and an air guide pipe, wherein the high-pressure turbine rotor is coaxially connected with the high-pressure compressor rotor, the front end of the air guide pipe is arranged in a disk center hole of the high-pressure compressor rotor, the rear section of the air guide pipe is arranged on a rear shaft of the high-pressure turbine rotor, and the air guide pipe is any air guide pipe for the high-pressure rotor.

According to the cognition of the inventor on the defects of the existing air guide pipe, the novel air guide pipe is provided and is used for a gas turbine including an aircraft engine, a structure that two layers which are contacted with each other at intervals are arranged between an outer layer and an inner layer is adopted, the vibration energy of the air guide pipe can be absorbed by taking the mutual friction between the two layers as damping when the engine works, and the novel air guide pipe has the effect of better vibration resistance; and meanwhile, the inner layer and the outer layer are filled with heat insulation materials, so that high-temperature air-entraining airflow can be separated from the inner cavity, and a better heat insulation effect is achieved.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

fig. 1 is a schematic view of a high pressure rotor.

Fig. 2 is a longitudinal sectional view of an air duct.

Fig. 3 is a cross-sectional view of an air duct.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

The air duct 5 in fig. 1 is replaced by the air duct shown in fig. 2 and 3, and the air duct after replacement can absorb the vibration energy transmitted by the upstream component by using the mutual friction between the two layers of the middle layer as the damping when the engine works, thereby having the effect of better vibration resistance; meanwhile, the heat insulation material filled between the outer layer and the inner layer can effectively prevent heat exchange between the inside and the outside, and has better heat insulation effect.

Fig. 3 is a sectional view taken along line a-a of fig. 2. Fig. 2 is a sectional view taken in a horizontal direction or a vertical direction in fig. 3.

As shown in fig. 2 and 3, the air duct for a high-pressure rotor includes an outer layer 6, an inner layer 7, an intermediate layer, and an insulating material 10. The intermediate layer is two

layers

8, 9, with layer 8 being on the opposite outer periphery side and layer 9 being on the other opposite inner periphery side.

The outer layer 6 extends from the front end to the rear end of the air duct, and the inner layer 7 also extends from the front end to the rear end of the air duct. The outer layer 6 and the inner layer 7 are directly welded into a whole at the front end and the rear end respectively and are used as mounting seats, so that the mounting seats are conveniently arranged on a disk core hole of a high-pressure compressor rotor and a rear shaft of the high-pressure turbine rotor. The intermediate layer extends substantially at a location other than the mounting seat of the air duct.

The transverse cross-section of each

layer

8, 9 of the intermediate layer comprises fixed parts and non-fixed parts arranged alternately in the circumferential direction. For example, layer 8 includes alternating fixed portions 81 and non-fixed portions 82. The layer 9 comprises a fixed part 91 and a non-fixed part 92 arranged at the bottom. In the embodiment shown, both

layers

8, 9 are corrugated, having peaks and valleys, with the anchoring portions 91 of layer 9 being valleys and the non-anchoring portions 92 being peaks, and the anchoring portions 81 of layer 8 being peaks and the non-anchoring portions 82 being valleys. The layer 8 and the outer layer 6 are connected and fixed at intervals, and similarly, the layer 9 and the inner layer 7 are connected and fixed at intervals. For example, each fixed portion 81 of the layer 8 is welded or integrally formed by additive manufacturing to the inner wall surface of the outer layer 6, and each non-fixed portion 82 of the layer 8 forms a cavity between the inner wall surface of the outer layer 6 and the cavity, which is filled with the heat insulating material 10. For another example, each fixed portion 91 of the layer 9 is welded or integrally formed with the outer wall surface of the inner layer 7 by additive manufacturing, and a cavity is formed between each non-fixed portion 92 of the layer 9 and the outer wall surface of the inner layer 7, and the cavity is also filled with the heat insulating material 10.

The intermediate layers are each secured to the respective outer and

inner layers

6, 7 by spaced connections, which advantageously increases the contact between the non-secured

portions

82, 92. During the operation of the engine, when the upstream component transmits vibration or vibration energy excited when the bleed air flow passes through the wall of the air duct, the non-fixed

portions

82, 92 rub against each other to absorb the vibration energy when the air duct rotates at high speed and the vibration energy excited when the bleed air flow passes through the wall of the air duct as damping, thereby having better vibration resistance. On the other hand, the heat insulating material is provided through the cavity of the wall surface between each of the

non-fixing portions

82, 92 and the corresponding outer layer 6, inner layer 7, and the heat insulating material 10 is provided in the cavity formed between the

fixing portions

81, 91, these cavities provide a space for providing the heat insulating material, and the heat transfer inside and outside the air duct is blocked by the heat insulating material, so that the heat exchange inside and outside is effectively prevented, and a preferable heat insulating effect is obtained.

From the foregoing description, the cross-sectional shape of each layer of the intermediate layer is not necessarily a wave shape as shown in fig. 3, but may be other shapes.

When the connection fixing parts are welded, the outer layer 6, the inner layer 7 and the middle layer are made of metal materials with high specific strength and good weldability, such as titanium alloy, high-temperature alloy and the like. In addition, the thermal insulation material 10 is made of a material with a low thermal conductivity and a low density, such as polyurethane foam, phenolic foam, etc. The thermal insulation material can reduce the thermal radiation influence of high-temperature gas on other cooling gases, and further reduce the over-temperature risk of the low-pressure shaft and the rear-end high-temperature component.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims

1. An air duct for a high pressure rotor of a gas turbine, comprising:

an outer layer;

an inner layer extending within the outer layer;

an intermediate layer disposed between the outer layer and the inner layer; and

a thermal insulation material;

the middle layer comprises two layers, the transverse section of each layer comprises fixing parts and non-fixing parts which are alternately arranged along the circumferential direction, one non-fixing part positioned on the opposite outer circumferential side in the two layers is opposite to and in surface contact with the other non-fixing part positioned on the opposite inner circumferential side, the one fixing part and the other fixing part are opposite to each other to form a cavity, the one fixing part is fixedly connected with the outer layer, a cavity is formed between the non-fixing part of the one part and the outer layer, the other fixing part is fixedly connected with the inner layer, and a cavity is formed between the non-fixing part of the one part and the outer layer;

the heat insulating material is filled in the cavity.

2. An air guide duct for a high pressure rotor according to claim 1, wherein each of the intermediate layers has a wave shape in transverse cross section, and one of the valleys on the outer peripheral side is in surface contact with the other of the valleys on the inner peripheral side, the one of the peaks and the other of the valleys form a cavity in opposition to each other, the one of the peaks is fixedly connected to the outer layer, a cavity is formed between the one of the valleys and the outer layer, the other of the valleys is fixedly connected to the inner layer, and a cavity is formed between the one of the peaks and the outer layer.

3. The air duct for a high pressure rotor as claimed in claim 1, wherein said connection is fixed by welding.

4. The air duct for a high pressure rotor as claimed in claim 1, wherein the material of the outer layer, the inner layer, the intermediate layer is selected from a titanium alloy or a high temperature alloy.

5. The air duct for a high pressure rotor as claimed in claim 1, wherein the heat insulating material is selected from a polyurethane foam or a phenolic foam.

6. An air duct for a high pressure rotor as set forth in claim 1, wherein said outer layer and said inner layer are directly welded to be one body at both ends of the air duct.

7. A high-pressure rotor of a gas turbine, comprising a high-pressure compressor rotor, a high-pressure turbine rotor coaxially connected with the high-pressure compressor rotor, and an air conduit, wherein the front end of the air conduit is installed in a disk core hole of the high-pressure compressor rotor, and the rear section of the air conduit is installed on a rear shaft of the high-pressure turbine rotor, and the air conduit is the air conduit for the high-pressure rotor as claimed in any one of claims 1 to 6.