CN117072259A

CN117072259A - Interstage casing of turbine of aeroengine and radiation-proof heat insulation structure

Info

Publication number: CN117072259A
Application number: CN202210506368.XA
Authority: CN
Inventors: 梁俐俐; 高妍; 张劲草
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2022-05-10
Filing date: 2022-05-10
Publication date: 2023-11-17

Abstract

The invention provides a radiation-proof heat insulation structure which is used for an interstage casing of an aeroengine turbine. The radiation-proof heat insulation structure also comprises a heat insulation plate and a fastener. The heat insulating plate is arranged between the casing body and the flange body and comprises a straight plate part and a concave plate part which is concave from the straight plate part towards one side of the casing body or the flange body. The heat insulating plate is provided with a mounting hole, the casing body is provided with a perforation, and the fastener passes through the perforation and the mounting hole to fasten and support the heat insulating plate on the casing body. The invention also provides an aircraft engine turbine interstage casing comprising the radiation-proof heat insulation structure. The radiation-proof heat insulation structure can reduce radiation heat exchange in the interstage casing of the turbine of the aeroengine.

Description

Interstage casing of turbine of aeroengine and radiation-proof heat insulation structure

Technical Field

The invention relates to an interstage casing of an aeroengine turbine, in particular to a radiation-proof heat insulation structure.

Background

During the actual working process of the aeroengine, radiation heat exchange exists besides heat conduction between solids and convection heat exchange between the surface of the solids and fluid. Radiation is the phenomenon that electromagnetic waves transfer energy, and objects continuously emit heat radiation to the space and absorb radiation continuously, so that heat transfer among the objects in a radiation mode is caused.

In general, components near the main flow gas side are affected by high temperature gas, the temperature is high, and components far from the main flow side are relatively low. With the continuous development of aero-engine technology, the temperature difference is further increased, and the radiation heat exchange quantity is in direct proportion to the difference value of the absolute temperature fourth power, so that the radiation heat exchange is generally not negligible in a cavity with large temperature difference near the main flow wall surface of the aero-engine.

The turbine interstage casing of an aeroengine, which is one of the main bearing frames, is located between the high pressure turbine and the low pressure turbine, and plays an important role in the whole aeroengine. The rectifying blade edge plate of the interstage casing is close to the main flow fuel gas, and the temperature is high; the outer casing of the interstage casing is close to the core cabin, so that the temperature is low; therefore, the two have larger temperature difference and the radiation heat exchange quantity is large.

Accordingly, the inventors analyzed that the radiation protection, insulation structure could be designed to reduce the radiative heat transfer, thus reducing the risk of the high Wen Yuanban to low temperature case radiation causing the case to exceed the long term allowable temperature of the material.

Disclosure of Invention

The invention aims to provide a radiation-proof heat insulation structure which can reduce radiation heat exchange in an interstage casing of a turbine of an aeroengine.

The invention provides a radiation-proof heat insulation structure which is used for an interstage casing of an aeroengine turbine. The radiation-proof heat insulation structure also comprises a heat insulation plate and a fastener. The heat insulating plate is arranged between the casing body and the flange plate body, and comprises a straight plate part and a concave plate part which is concave from the straight plate part towards one side of the casing body or the flange plate body. The heat insulating plate is provided with a mounting hole, the casing body is provided with a perforation, and the fastener passes through the perforation and the mounting hole to fasten and support the heat insulating plate on the casing body.

In one embodiment, the mounting hole is provided in the concave plate portion of the heat shield.

In one embodiment, the flat plate portion of the heat shield is provided with a plurality of vent holes for the passage of bleed air.

In one embodiment, the radiation protection and thermal insulation structure further comprises a first thermal insulation gasket disposed between the thermal insulation plate and the casing body.

In one embodiment, the concave plate portion forms a concave pit recessed toward one side of the deck body. The fastener passes through the mounting hole, the first heat insulation gasket and the perforation in sequence to fasten the first heat insulation gasket between the pit bottom of the pit and the casing body.

In one embodiment, the heat shield and the case body are spaced apart from each other.

In one embodiment, the fastener includes a threaded bolt and a nut, the shank of the bolt passing through the aperture and the mounting hole, the nut being located on the opposite side of the heat shield from the case body. The radiation-proof heat insulation structure further comprises a second heat insulation gasket, and the second heat insulation gasket is arranged between the heat insulation plate and the nut.

In one embodiment, the fairing blade platform further includes a front securing structure connected to the front end of the platform body. The outer casing comprises a front protruding structure, and the front protruding structure protrudes downwards from the front end of the casing body. The radiation-proof heat insulation structure also comprises a rear fixing structure. The front fixing structure is connected with the front protruding structure, two ends of the rear fixing structure are respectively connected with the rear end of the flange plate body and the rear end of the casing body, thereby forming a surrounding space between the outer casing and the rectifying blade flange plate, and the heat insulation plate is arranged in the surrounding space.

In one embodiment, the emissivity of the fairing blade edge plate and the outer casing is 0.6-0.8. The emissivity of the heat insulating plate is below 0.05.

The invention also provides an aircraft engine turbine interstage casing which comprises the radiation-proof heat insulation structure.

In the radiation-proof heat insulation structure, the heat insulation plate is arranged between the casing body and the flange plate body, so that radiation heat exchange in the interstage casing of the turbine of the aeroengine can be effectively reduced, radiation effect is weakened, the influence of the radiation heat exchange effect is reduced, and the safety of the engine is further improved. And further, by enabling the heat insulation plate to comprise the concave plate part, the heat insulation plate can expand towards one side after being heated, and breakage of the heat insulation plate caused by overlarge thermal stress of the heat insulation plate is avoided.

Drawings

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

FIG. 1 is a schematic view of an exemplary radiation protective thermal insulation structure.

Fig. 2 is an enlarged view of a portion of the vicinity of the fastener of fig. 1.

FIG. 3 is a plan view of an exemplary radiation shield.

Detailed Description

The present invention will be further described with reference to the following detailed description and the accompanying drawings, in which more details are set forth in order to provide a thorough understanding of the present invention, but it will be apparent that the present invention can be embodied in many other forms than described herein, and that those skilled in the art may make similar generalizations and deductions depending on the actual application without departing from the spirit of the present invention, and therefore should not be limited in scope by the context of this detailed description.

For example, a first feature described later in this specification may be formed above or on a second feature, and may include embodiments in which the first and second features are formed in direct contact, as well as embodiments in which additional features are formed between the first and second features, such that no direct contact between the first and second features is possible. Further, where a first element is described as being coupled or combined with a second element, the description includes embodiments in which the first and second elements are directly coupled or combined with each other, and also includes embodiments in which one or more other intervening elements are added to indirectly couple or combine the first and second elements with each other.

Radiation is one of the three forms of heat transfer, the presence of which is not negligible, particularly in areas of high temperature and large temperature differences, the effect of which is even more non-negligible. The temperature difference between the outer casing of the engine interstage casing and the edge plate of the rectifying vane is larger, the radiation heat exchange quantity is larger, and the temperature rise caused by the radiation effect is not negligible. That is, the actual operating engine component wall temperature has a non-negligible effect on the high temperature component radiation, in addition to the effects of thermal conduction and convection. Especially in the case where the temperature difference between the high and low temperature parts is large, the radiant energy of the high temperature parts will cause a rapid temperature rise of the low temperature parts, resulting in a problem in strength.

According to the invention, through the design of the heat insulation plate, the heat resistance of the heat exchange path is increased, so that the radiation heat transfer is reduced, and the risk that the outer casing of the turbine interstage casing exceeds the long-term allowable temperature of materials is reduced.

FIG. 1 illustrates a schematic view of an exemplary radiation protective thermal insulation structure 10 for an aircraft engine turbine interstage casing. Fig. 2 shows a partially enlarged configuration in the vicinity of a fastener 4 to be described later. The invention also provides an aircraft engine turbine interstage casing, which comprises the radiation-proof heat insulation structure 10. Fig. 3 shows a planar construction of the heat shield 3.

It is to be understood that the drawings are by way of example only and are not drawn to scale and should not be construed to limit the true scope of the invention.

The radiation protection and heat insulation structure 10 comprises an outer casing 1 of the interstage casing and a rectifying vane flange plate 2. The outer casing 1 includes a casing body 11. The fairing blade platform 2 includes a platform body 21.

The radiation protection and heat insulation structure 10 further comprises a heat insulation plate 3 and a fastener 4. The fastener 4 may comprise, for example, a screw-fit bolt 41 and a nut 42.

The heat shield 3 is disposed between the casing body 11 and the flange body 21. The heat insulating plate 3 includes a flat plate portion 31 and a concave plate portion 32. The concave plate portion 32 is concave from the flat plate portion 31 toward the case body 11 or the flange body 21. That is, the concave plate portion 32 is recessed toward the case body 11 side, or recessed toward the deck body 21 side. The concave plate portion 32 may also be considered to have a U-shape.

The heat shield 3 is provided with mounting holes 33. The casing body 11 is provided with a through hole 110, and the fastener 4 passes through the through hole 110 and the mounting hole 33 to fasten and support the heat insulating plate 3 to the casing body 11.

In the radiation-proof heat insulation structure 10, a heat insulation plate 3 is disposed between the casing body 11 and the flange body 21. The heat insulating board 3 may also be called a radiation protection heat insulating board, and the radiation heat exchange amount can be greatly reduced by increasing the space radiation heat resistance. Moreover, by providing the heat insulating plate 3 to include the concave plate portion 32 in a concave shape in addition to the flat plate portion 31, the heat insulating plate 3 can be expanded toward one side after being heated, and breakage of the heat insulating plate 3 due to excessive thermal stress of itself is avoided.

The radiation-proof heat insulation structure 10 can effectively reduce the overtemperature risk of the interstage casing outer casing 1 through a simple structure, ensure the safety, prolong the service life and eliminate the influence caused by radiation.

In the illustrated embodiment, the mounting holes 33 may be provided in the concave plate portion 32 of the heat insulating plate 3. That is, the heat insulating plate 3 is provided with dimples at fastening positions of the fasteners 4. This facilitates the installation of the insulation blanket 51 to be mentioned later.

It is to be understood that the use of specific words to describe embodiments of the invention, such as "one embodiment," "another embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the invention. Thus, it should be emphasized and should be appreciated that two or more references to "one embodiment" or "another embodiment" in this specification at different positions are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the invention may be combined as suitable.

In the illustrated embodiment, the flat plate portion 31 of the heat shield 3 may be provided with a plurality of vent holes 311 (shown in fig. 3) for the passage of bleed air. It is understood that "plurality" herein means more than two, including two, three, four, five, etc. The heat insulating plate 3 comprises vent holes 311, so that the normal exhaust of the original vent holes of the outer casing 1 of the interstage casing can not be influenced. It will be appreciated that the insulating panel 3 is shown in figure 3 as a circular ring shape, in essence as a truncated cone shape, i.e. a shape after the cone has been truncated by a plane. In fig. 3, each circle of ventilation holes 311 and each circle of mounting holes 33 are uniformly distributed in the circumferential direction.

In the illustrated embodiment, the radiation protective insulating structure 10 may also include a first insulating spacer 51. The first insulation blanket 51 may be disposed between the insulation plate 3 and the casing body 11. When the heat insulating spacer 51 with low thermal conductivity is installed between the heat insulating plate 3 and the outer casing 1, even if the temperature rises after the heat insulating plate 3 absorbs the radiant heat of the rectifying vane flange plate 2, the heat insulating plate 3 can be prevented from further conducting the heat to the outer casing 1. For example, the thermal conductivity of the insulating spacer 51 is lower than 0.5W/(mK).

It will be appreciated that the terms "first," "second," etc. are used herein to define features, and are merely for convenience in distinguishing between corresponding features, as no special meaning is given to the terms above, nor should they be construed as limiting the scope of the present invention.

In the illustrated embodiment, the concave plate portion 32 may form a concave pit recessed toward one side of the deck body 21. It is also considered that the concave plate portion 32 is a convex structure protruding toward the deck body 21 side with respect to the flat plate portion 31. In the illustrated embodiment, the fastener 4 (specifically, the bolt 41) may pass through the mounting hole 33, the first insulation pad 51, and the perforated hole 110 in order to fasten the first insulation pad 51 between the bottom 321 of the pit (formed by the aforementioned concave plate portion 32) and the casing body 11. In the above-described structure, the space formed by the concave plate portion 32 is fully utilized to place the heat insulating gasket 51, so that the structure is compact.

In the illustrated embodiment, the heat shield 3 and the casing body 11 may be spaced apart from each other. That is, the heat shield 3 and the case body 11 are not in contact with each other, so that the radiation protection effect can be enhanced. In fig. 2, the heat shield 3 and the flange body 2 may be spaced apart from each other, and the gap between the heat shield 3 and the flange body 2 is larger than the gap between the heat shield 3 and the casing body 11, in other words, the heat shield 3 is closer to the casing body 11 than the flange body 2.

In the illustrated embodiment, the shank 410 of the bolt 41 may pass through the aperture 110 and the mounting hole 33. The nut 42 may be located on the opposite side of the heat shield 3 from the case body 11, i.e., on the same side of the heat shield 3 as the flange body 21. The radiation protective insulating structure 10 may also include a second insulating spacer 52. A second insulation blanket 52 may be disposed between the insulation panel 3 and the nut 42.

The heat insulating plate 3 is connected by bolts 41 and is mounted on the inner side of the outer casing 1 of the interstage casing, so that the structure is simple and the mounting is convenient.

In the illustrated embodiment, the fairing blade platform 2 may further include a forward securing structure 22, the forward securing structure 22 being coupled to the forward end of the platform body 21. The outer casing 1 may include a front protruding structure 12, the front protruding structure 12 protruding downward from the front end of the casing body 1. The radiation protective and heat insulating structure 10 may also comprise a rear fixing structure 7. The front fixing structure 22 may be connected with the front projecting structure 12, and both ends of the rear fixing structure 7 are connected with the rear end of the flange plate body 21 and the rear end of the casing body 1, respectively, thereby forming an enclosure space S0 between the outer casing 1 and the rectifying vane flange plate 2. The heat insulating plate 3 may be disposed in the surrounding space S0. Like this, make full use of the girth space S0 between outer receiver 1 and the rectification blade edge plate 2 sets up heat insulating board 3, compact structure, radiation protection is effectual moreover.

It will be appreciated that the use of spatial relationship words such as "front," "rear," "upper," "lower," etc. to describe the relationship of one element or feature to another element or feature illustrated in the figures is by reference to the orientation of FIG. 1 for ease of description, and that these spatial relationship words are intended to encompass other orientations of the element or component in use or operation in addition to the orientation depicted in the figures. For example, if the component in the figures is turned over, elements described as "before" other elements or features would then be oriented "after" the other elements or features, and the spatially relative descriptors used herein should be interpreted accordingly.

In the illustrated embodiment, the emissivity of the fairing blade platform 2 and the outer casing 1 may be 0.6-0.8. The emissivity of the heat shield 3 may be 0.05 or less.

Through practical analysis, when the emissivity of the heat insulating plate 3 is consistent with that of the outer casing 1 and the rectifying vane flange plate 2, for example, the emissivity is 0.7, and the radiant heat is reduced by half compared with the radiant heat transfer when the heat insulating plate 3 is not added. When the emissivity of the heat insulating plate 3 is 0.05, the radiation heat exchange amount is 1/22 of that of the heat insulating plate 3, and the radiation heat can be greatly reduced.

In one embodiment, the surface of the heat shield 3 may be polished to have a low emissivity. The heat shield 3 is attached to the inner wall surface of the interstage casing outer casing 1 by a fastener 4, thereby reducing the absorption of radiant heat from the high temperature member and reducing the influence of the high temperature heat source.

In the radiation-proof heat insulation structure 10, through the heat insulation plate 3 with a simple structural form, the radiation heat exchange quantity is greatly reduced in a mode of increasing the space radiation heat resistance, so that the overtemperature risk of the outer casing 1 of the interstage casing is reduced, the safety is ensured, the service life is prolonged, and the influence caused by radiation is greatly reduced.

While the invention has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the invention, as will occur to those skilled in the art, without departing from the spirit and scope of the invention. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present invention fall within the protection scope defined by the claims of the present invention.

Claims

1. A radiation protection and heat insulation structure is used for an interstage casing of an aeroengine turbine, and comprises an outer casing of the interstage casing and a rectifying blade flange plate, wherein the outer casing comprises a casing body, the rectifying blade flange plate comprises a flange plate body,

the radiation protection heat insulation structure further includes:

the heat insulation plate is arranged between the casing body and the flange plate body and comprises a straight plate part and a concave plate part which is concave from the straight plate part towards one side of the casing body or the flange plate body; and

the fastener, the heat insulating board is provided with the mounting hole, the receiver body is provided with the perforation, the fastener pass the perforation with the mounting hole will the heat insulating board fastening support in the receiver body.

2. The radiation protective and heat insulating structure of claim 1, wherein said mounting holes are provided in said concave plate portion of said heat shield.

3. The radiation-resistant, thermally insulating structure of claim 1, wherein said flat plate portion of said insulating panel is provided with a plurality of vent holes for the passage of bleed air.

4. The radiation-protective and thermally-insulating structure of claim 1, further comprising a first thermal-insulating gasket disposed between the thermal-insulating panel and the casing body.

5. The radiation protection and thermal insulation structure according to claim 4, wherein the concave plate portion forms a concave pit recessed toward one side of the flange body;

the fastener passes through the mounting hole, the first heat insulation gasket and the perforation in sequence to fasten the first heat insulation gasket between the pit bottom of the pit and the casing body.

6. The radiation-resistant, thermally insulating structure of claim 1, wherein said insulating panel and said casing body are spaced apart from one another.

7. The radiation-resistant, thermally insulating structure of claim 1, wherein said fastener comprises a threaded mating bolt and nut, a shank of said bolt passing through said aperture and said mounting hole, said nut being located on an opposite side of said insulating panel from said receiver body;

the radiation-proof heat insulation structure further comprises a second heat insulation gasket, and the second heat insulation gasket is arranged between the heat insulation plate and the nut.

8. The radiation protected thermal insulation structure of claim 1, wherein said fairing blade platform further comprises a front securing structure connected to a front end of said platform body; the outer casing comprises a front protruding structure, and the front protruding structure protrudes downwards from the front end of the casing body; the radiation-proof heat insulation structure also comprises a rear fixing structure;

the front fixing structure is connected with the front protruding structure, two ends of the rear fixing structure are respectively connected with the rear end of the flange plate body and the rear end of the casing body, thereby forming a surrounding space between the outer casing and the rectifying blade flange plate, and the heat insulation plate is arranged in the surrounding space.

9. The radiation protection and heat insulation structure according to claim 1, wherein the emissivity of the rectifying vane flange and the outer casing is 0.6-0.8;

the emissivity of the heat insulating plate is below 0.05.

10. An aircraft engine turbine interstage casing comprising a radiation protection and thermal insulation structure as claimed in any one of claims 1 to 9.