Turbine outer ring connection structure, midframe, gas turbine engine and connection method

Abstract

The application provides a turbine outer ring connecting structure, a middle casing, a gas turbine engine and a connecting method. The turbine outer ring connecting structure comprises: a turbine outer ring member, comprising a turbine outer ring body and an extension part, the extension part comprising axially adjacent first and second rib plates extending radially outward from the turbine outer ring body; a middle casing comprising a first casing part, a second casing part and a connecting part arranged between the first and second casing parts; wherein the first casing part is detachably connected to the first rib plate, the second casing part is detachably connected to the second rib plate, and the connecting part comprises an extendable section, the extendable section being detachably connected to the first and second casing parts on both axial sides; and the thermal expansion coefficient of the turbine outer ring member is less than the thermal expansion coefficient of the middle casing. The effect of preventing thermal mismatch from generating thermal stress is achieved.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more particularly to a turbine outer ring connection structure, a central bearing casing, a gas turbine engine, and a connection method thereof. Background Technology

[0002] Ceramic matrix composites (CMCs) are a type of composite material made by combining ceramics as the matrix with various fibers. The ceramic matrix can be high-temperature structural ceramics such as silicon nitride and silicon carbide. CMCs possess excellent properties such as high temperature resistance, high strength and stiffness, low density and relatively light weight, and corrosion resistance. They have been applied to high-temperature hot-end components of aero-engines, such as outer rings, tail nozzle systems, and flame tubes. They are considered the first choice for replacing high-temperature alloys and achieving weight reduction and efficiency improvement in new advanced engines. Summary of the Invention

[0003] The purpose of this invention is to provide a turbine outer ring connection structure.

[0004] Another object of the present invention is to provide a gas turbine engine.

[0005] Another object of the present invention is to provide a central support casing.

[0006] Another object of the present invention is to provide a connection method.

[0007] According to one aspect of the present invention, a turbine outer ring connection structure includes: a turbine outer ring component, comprising a turbine outer ring body and an extension portion, the extension portion including an axially adjacent first rib and a second rib extending radially outward from the turbine outer ring body; a central bearing casing, comprising a separately disposed first casing portion, a second casing portion, and a connecting portion located between the two; wherein the first casing portion is detachably connected to the first rib, the second casing portion is detachably connected to the second rib, and the connecting portion includes a telescopic section, the telescopic section being detachably connected to the first casing portion and the second casing portion on its axial sides respectively; the coefficient of thermal expansion of the turbine outer ring component is less than the coefficient of thermal expansion of the central bearing casing.

[0008] The technical solution of this application achieves the adjustment of the axial dimensions of the intermediate bearing casing and the turbine outer ring by setting a telescopic section. When the engine is running, under high temperature field conditions, the intermediate bearing casing is allowed to undergo axial displacement, preventing high stress from the axial constraint between the intermediate bearing casing and the turbine outer ring.

[0009] According to one or more embodiments of the turbine outer ring connection structure, the first rib and the second rib respectively have a first connecting hole and a second connecting hole; the first casing portion and the second casing portion of the intermediate bearing casing respectively have a third connecting hole corresponding to the first connecting hole and a fourth connecting hole corresponding to the second connecting hole; the turbine outer ring connection structure further includes a first connector and a second connector; wherein, the first connector connects the first connecting hole and the third connecting hole, the first rib is tightly connected to the first casing portion in an axial plane, the first rib is located on the axial downstream side of the first casing portion, and an elastic element is provided at the contact position between the first connector and the first rib; the second casing portion includes a first segment and a second segment, the fourth connecting hole includes a first hole segment and a second hole segment, there is an axial space between the first segment and the second segment, the second rib is located in the axial space, and the axial dimension of the second rib is smaller than the dimension of the axial space, and the second connector sequentially connects the first hole segment, the second connecting hole, and the second hole segment of the fourth connecting hole in an axial upstream to downstream direction.

[0010] According to one or more embodiments of the turbine outer ring connection structure, the turbine outer ring connection structure includes a cold state and a hot state:

[0011] In the cold state, the first casing portion is tightly connected to the first rib, the first section of the second casing portion is tightly connected to the second rib, and the second section of the second casing portion has a first axial gap with the second rib;

[0012] In the hot state, the first casing portion is tightly connected to the first rib, the first section of the second casing portion is tightly connected to the second rib, and the second section of the second casing portion and the second rib have a second axial gap, which is smaller than the first axial gap.

[0013] According to one or more embodiments of the turbine outer ring connection structure, the first segment of the second casing includes a first body and a first protrusion, the second segment includes a second body and a second protrusion, the first protrusion extends axially downstream from the first body, and the second protrusion extends axially upstream from the second body, the first protrusion and the second protrusion are used to axially limit the second rib.

[0014] According to one or more embodiments of the turbine outer ring connection structure, the thermal expansion coefficients of the first connector and the second connector are the same as those of the intermediate bearing casing, and the first connector and the second connector are respectively clearance fits with the first connecting hole and the second connecting hole.

[0015] According to one or more embodiments of the turbine outer ring connection structure, the first connecting hole, the second connecting hole, the third connecting hole, and the fourth connecting hole are arranged coaxially.

[0016] According to one or more embodiments of the turbine outer ring connection structure, the first segment includes a first segment body and a first segment connector, the second segment includes a second segment body and a second segment connector, the first segment connector has a first hole segment of the fourth connection hole, the second segment connector has a second hole segment of the fourth connection hole, there is an axial space between the first segment connector and the second segment connector, the second rib is located in the axial space, and the axial dimension of the second rib is smaller than the dimension of the axial space; the first segment body and the second segment body are detachably fixedly connected with their surfaces in close contact, and the first segment body is detachably connected to the connection part.

[0017] According to one or more embodiments of the turbine outer ring connection structure, the first casing portion includes a first casing portion body and a first mounting portion, the first mounting portion being detachably connected to the first rib, and the first casing portion body having a cold air passage that connects the space defined by the intermediate bearing casing and the turbine outer ring component.

[0018] According to one or more embodiments of the turbine outer ring connection structure, the connecting portion further includes a first connecting portion and a second connecting portion, which are respectively connected to the axial ends of the telescopic section. The first connecting portion and the second connecting portion have a fifth connecting hole and a sixth connecting hole, respectively. The first casing portion and the second casing portion have a seventh connecting hole and an eighth connecting hole, respectively. The turbine outer ring connection structure further includes a third connecting member and a fourth connecting member. The third connecting member connects the fifth connecting hole and the seventh connecting hole to connect the first casing portion and the first connecting portion. The fourth connecting member connects the sixth connecting hole and the eighth connecting hole to connect the second casing portion and the second connecting portion.

[0019] In one or more embodiments of the turbine outer ring connection structure, the expandable section is corrugated.

[0020] According to one or more embodiments of the turbine outer ring connection structure, the turbine outer ring is a ceramic matrix composite material, and the intermediate bearing casing is a high-temperature alloy.

[0021] According to another aspect of the present invention, a gas turbine engine includes the turbine outer ring connection structure as described above.

[0022] According to another aspect of the present invention, a mid-frame housing includes a first housing portion, a second housing portion, and a connecting portion located between the two portions; wherein the connecting portion includes a telescopic section, the telescopic section being detachably connected to the first housing portion and the second housing portion on both axial sides respectively.

[0023] According to another aspect of the present invention, a connection method is used to install a first annular member onto a second annular member coaxial with it, wherein the first annular member is made of a first material, the second annular member is made of a second material, and the coefficient of thermal expansion of the first material is less than that of the second material, comprising:

[0024] The first annular member is provided with an axially adjacent first rib and a second rib extending radially outward from the first annular member, and the two ribs respectively have a first connecting hole and a second connecting hole;

[0025] The second annular component is configured as a separate first part, a second part, and a connecting part located between the two for connecting the two;

[0026] The first part is configured to be detachably connected to the first rib, and the second part is configured to be detachably connected to the second rib. The connecting part includes a telescopic section whose length in the axial direction is telescopic. The telescopic section is detachably connected to the first part and the second part on both sides in the axial direction, respectively. The coefficient of thermal expansion of the first annular part is less than that of the second annular part. Attached Figure Description

[0027] The above-described and other features, properties, and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features. It should be noted that these drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection actually claimed by the present invention, wherein:

[0028] Figure 1 This is a schematic diagram of the turbine outer ring connection structure according to one embodiment;

[0029] Figure 2 This is a schematic diagram of the turbine outer ring connection structure from another perspective of one embodiment;

[0030] Figure 3 This is a schematic diagram of the structure of the connecting part according to one embodiment. Detailed Implementation

[0031] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0032] In the following description, the orientation or positional relationship indicated by the terms "radial", "axial", "inner", "outer" or other directional terms is based on the orientation or positional relationship shown in the accompanying drawings and is only for the purpose of describing the invention and simplifying the description, and is not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention.

[0033] Furthermore, this application uses specific terms to describe its embodiments. For example, "an embodiment" and / or "one embodiment" refers to a particular feature, structure, or characteristic associated with at least one embodiment of this application. Therefore, it should be emphasized and noted that "an embodiment" or "one embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0034] Currently, with the increasing demands for weight reduction and efficiency improvement in aero engines, further improvements to engines are needed.

[0035] The inventors of this application, through in-depth research, discovered that CMC ceramic matrix composites and metal materials have significantly different thermal conductivity and coefficients of thermal expansion. Under high-temperature environments, metal materials deform considerably, while CMC ceramic matrix composites deform less. Therefore, the connection between CMC ceramic matrix composites and metal materials is particularly important. It must ensure the structure's function, load transfer, and displacement restriction, while also preventing the CMC ceramic matrix composite from failing due to inconsistent deformation between the metal and CMC materials. Therefore, when using CMC ceramic matrix composite outer rings in aero-engine components, the thermal mismatch connection problem between the outer ring and the metal component needs to be considered. Thermal mismatch refers to the phenomenon where adjacent materials or components with different coefficients of thermal expansion exhibit inconsistent thermal expansion deformation during temperature changes within the same system. Unresolved thermal deformation mismatch can cause significant thermal mismatch stress within the system.

[0036] Based on the above considerations, the inventors, after in-depth research, designed a turbine outer ring connection structure. By incorporating a telescopic section, the axial dimensions of the intermediate bearing casing and the turbine outer ring can be adjusted. During engine operation, under high-temperature conditions, axial displacement of the intermediate bearing casing is allowed, preventing high stress from the axial constraints between the intermediate bearing casing and the turbine outer ring. Furthermore, the turbine outer ring's structure resembles a π-shape, facilitating manufacturing.

[0037] Although the turbine outer ring connection structure disclosed in the embodiments of this application is applicable to gas turbine engines to prevent thermal mismatch and thermal stress, it is not limited thereto. As long as the connection is to prevent high stress caused by uneven deformation, the connection structure disclosed in the embodiments of this application can be applied.

[0038] refer to Figure 1 As shown, in one embodiment, the turbine outer ring connection structure 100 may specifically include a turbine outer ring component 1 and a middle support casing 2. The turbine outer ring component 1 includes a turbine outer ring body 11 and an extension 12. The extension 12 includes an axially adjacent first rib 121 and a second rib 122 extending radially outward from the turbine outer ring body 11. The middle support casing 2 includes a separately configured first casing portion 21, a second casing portion 22, and a connecting portion 23 located between them. The first casing portion 21 is detachably connected to the first rib 121, and the second casing portion 22 is detachably connected to the second rib 122. The connecting portion 23 includes a telescopic section 230, which is detachably connected to the first casing portion 21 and the second casing portion 22 on both axial sides. The coefficient of thermal expansion of the turbine outer ring component 1 is less than that of the middle support casing 2.

[0039] The term "turbine outer ring 1" here refers to a component of an aero-engine that isolates the engine from the scouring of high-temperature combustion gases and maintains the structural integrity of the casing.

[0040] The term "middle support casing 2" here refers to the main load-bearing component of an aero-engine, which is a stationary part. It contains the engine blade when it detaches.

[0041] The beneficial effect of this embodiment is that by setting a telescopic section, the axial dimensions of the intermediate bearing casing and the turbine outer ring can be adjusted. When the engine is running, under high temperature field conditions, the intermediate bearing casing is allowed to undergo axial displacement, preventing high stress from the axial constraint between the intermediate bearing casing and the turbine outer ring.

[0042] refer to Figure 1 Combination Figure 2As shown, in some embodiments, the specific structure of the turbine outer ring connecting structure 100 may be that the first rib 121 and the second rib 122 respectively have a first connecting hole 311 and a second connecting hole 32. The first casing portion 21 and the second casing portion 22 of the intermediate bearing casing 2 respectively have a third connecting hole 5 corresponding to the first connecting hole 31 and a fourth connecting hole 6 corresponding to the second connecting hole 32. The turbine outer ring connecting structure 100 also includes a first connecting member 35 and a second connecting member 46. The first connecting member 35 connects the first connecting hole 31 and the third connecting hole 5. The first rib 121 and the first casing portion 21 are tightly connected in axial plane. The first rib 121 is located on the axial downstream side of the first casing portion 21. An elastic member 7 is provided at the contact position between the first connecting member 35 and the first rib 121. In some embodiments, such as Figure 2 As shown, the elastic element 7 is a spring washer.

[0043] The second casing 22 includes a first section 221 and a second section 222. The fourth connecting hole 6 includes a first hole section 601 and a second hole section 602. There is an axial space a between the first section 221 and the second section 222. The second rib 122 is located in the axial space a in the axial direction, and the axial dimension of the second rib 122 is smaller than the dimension of the axial space a. The second connector 46 sequentially connects the first hole section 601, the second connecting hole 32 and the second hole section 602 of the fourth connecting hole 6 in the axial direction from upstream to downstream.

[0044] The beneficial effects of this embodiment are that it divides the traditional integral engine casing into a modular design consisting of a first casing section, a second casing section, and a connecting section between the two, facilitating assembly and disassembly. By incorporating a telescopic section, the axial dimension of the engine casing can be adjusted, allowing axial displacement during engine operation and releasing axial stress. The addition of connecting components makes the entire connection structure more robust and easier to assemble and disassemble. The inclusion of elastic elements and axial space allows for axial deformation and displacement of both the engine casing and the turbine outer ring. The principle behind this is, for example... Figure 2As shown, the first casing portion 21 is tightly attached to the first rib plate 121. An elastic element 7 is provided between the first rib plate 121 and the first connecting member 35. When thermal mismatch occurs, the first casing portion 21 undergoes thermal deformation and shifts axially downstream, pushing the first rib plate 121. The first rib plate 121 compresses the elastic element 7 and also shifts axially until the elastic element 7 can no longer be compressed. The second rib plate 122 and the second segment 222 have axial space, allowing the first segment 221 to shift axially downstream, driving the second rib plate 122 to shift axially downstream until it fits against the second segment 222. This not only limits the positioning of the turbine outer ring component but also prevents the difference in thermal expansion coefficients between the intermediate casing and the turbine outer ring component, avoiding downstream deformation of the intermediate casing at high temperatures, which could generate high stress at the roots of the first and second rib plates and cause damage. In the installed state, it ensures sufficient structural strength; in the thermal mismatch state, it effectively prevents excessive stress.

[0045] In some embodiments, such as Figure 2 As shown, the first connector 35 and the second connector 46 are bolts.

[0046] Continue to refer to Figure 1 Combination Figure 2 As shown, in some embodiments, the turbine outer ring connection structure 100 may have a cold state and a hot state:

[0047] In the cold state, the first casing portion 21 is tightly connected to the first rib plate 121, and the first section 221 of the second casing portion 22 is tightly connected to the second rib plate 122. The second section 222 of the second casing portion 22 and the second rib plate 122 have a first axial clearance. This is the installed state, which ensures that the turbine outer ring connection structure is sufficiently robust and provides enough space for thermal deformation of the intermediate bearing casing, so that the turbine outer ring component can adaptively move according to the engine's operating conditions, releasing deformation and load, and preventing the generation of high stress.

[0048] In the hot state, the first casing portion 21 is tightly connected to the first rib plate 121, and the first section 221 of the second casing portion 22 is tightly connected to the second rib plate 122. The second section 222 of the second casing portion 22 and the second rib plate 122 have a second axial clearance, which is smaller than the first axial clearance, and can even be zero. When the engine is running, at high temperature, the thermal deformation of the intermediate bearing casing is greater than the thermal deformation of the turbine outer ring component, causing the entire casing to shift axially downstream. This reduces the axial clearance between the second section and the second rib plate until the second section and the second rib plate are in contact, thus limiting the turbine outer ring component and preventing damage caused by thermal mismatch stress.

[0049] In some embodiments, such as Figure 1 , Figure 2As shown, in the cold installation state, the middle support casing 2 is in radial contact with the upper end faces of the first rib 121 and the second rib 122. When the engine is running, under high temperature and internal and external cavity pressure, the middle support casing 2 deforms radially outward more than the turbine outer ring 1. The middle support casing 2 automatically releases a certain gap with the upper end faces of the first rib 121 and the second rib 122 to prevent the middle support casing 2 from generating excessive radial load on the turbine outer ring 1, which would cause damage. At the same time, it also plays a radial limiting role.

[0050] Continue to refer to Figure 1 Combination Figure 2 As shown, in some embodiments, the specific structure of the second housing portion 22 may be as follows: the first segment 221 of the second housing portion 22 includes a first body 2211 and a first protrusion 2212; the second segment 222 includes a second body 2221 and a second protrusion 2222. The first protrusion 2212 protrudes axially downstream from the first body 2211, and the second protrusion 2222 protrudes axially upstream from the second body 2221. The first protrusion 2212 and the second protrusion 2222 are used to axially limit the second rib plate 122. The beneficial effect of providing the first protrusion and the second protrusion is that it ensures the axial limitation of the second rib plate, while reducing the contact area with the rib plate, which facilitates ensuring the machining accuracy of the contact surface and makes it easier to process. In addition, this design can also reduce the weight of the second housing portion, achieving the effect of lightweight design.

[0051] Continue to refer to Figure 1 Combination Figure 2 As shown, in some embodiments, the specific structure of the turbine outer ring connection structure 100 may be that the thermal expansion coefficients of the first connector 35 and the second connector 46 are the same as those of the intermediate bearing casing 2, and the first connector 35 and the second connector 46 are respectively clearance fits with the first connecting hole 31 and the second connecting hole 32.

[0052] The phrase "same coefficient of thermal expansion" here means approximately the same. That is, the difference between the coefficients of thermal expansion of the first and second connecting parts and the intermediate bearing casing is negligible compared to the difference between the coefficients of thermal expansion of the turbine outer ring and the intermediate bearing casing. For example, the materials of the first and second connecting parts and the intermediate bearing casing may be exactly the same. Or, the materials of the first and second connecting parts and the intermediate bearing casing may all be nickel-based superalloys, but of different grades. This also falls under the category of "the coefficients of thermal expansion of the first and second connecting parts are the same as the coefficients of thermal expansion of the intermediate bearing casing."

[0053] The clearance fit effectively prevents thermal mismatch stress between the connecting hole and the connecting parts, and also facilitates the axial movement of the bearing casing and the outer ring of the turbine, preventing high stress at the roots of the first and second ribs from causing damage.

[0054] refer to Figure 2 As shown, in some embodiments, the turbine outer ring connecting structure 100 may have the first connecting hole 31, the second connecting hole 32, the third connecting hole 5, and the fourth connecting hole 6 arranged coaxially in the axial direction. The advantage of this arrangement is that it facilitates the movement of the turbine outer ring component and the intermediate bearing casing in the same direction, making it easier to release thermal stress.

[0055] refer to Figure 1 Combination Figure 2 As shown, in some embodiments, the specific structure of the second housing 22 can be as follows: the first segment 221 includes a first body 2201 and a first connecting body 2202; the second segment 222 includes a second body 2203 and a second connecting body 2204; the first connecting body 2201 has a first hole segment 601 with a fourth connecting hole 6; the second connecting body 2204 has a second hole segment 602 with a fourth connecting hole 6; there is an axial space a between the first connecting body 2202 and the second connecting body 2204; the second rib 122 is located within this axial space a, and the axial dimension of the second rib 122 is smaller than the dimension of the axial space a; the first body 2201 and the second body 2203 are detachably and fixedly connected face-to-face; the first body 2201 is detachably connected to the connecting part 23. This arrangement provides space for the axial displacement of the second housing, limits the position of the second rib, and facilitates assembly.

[0056] In some embodiments, such as Figure 1 , Figure 2 As shown, the first body 2201 has a ninth connecting hole 51, and the second body 2203 has a tenth connecting hole 52. The first body 2201 and the second body 2203 are connected by a fifth connector 9, which is a countersunk screw for easy disassembly and assembly.

[0057] Continue to refer to Figure 1 Combination Figure 2 As shown, in some embodiments, the specific structure of the first casing 21 may include a first casing body 211 and a first mounting part 212. The first mounting part 212 is detachably connected to the first rib 121. The first casing body 21 has a cold air passage 8, which connects the space b defined by the intermediate casing 2 and the turbine outer ring 1 to reduce the temperature of the turbine outer ring and the intermediate casing.

[0058] In some embodiments, such as Figure 2 As shown, the first connector 35 and the second connector 46 have a hole in the center that communicates with space b, which is used to discharge the cold air entering through the cooling channel 8, promote airflow, and make the cooling effect better.

[0059] refer to Figures 1 to 3 As shown, in some embodiments, the specific structure of the connecting part 23 may include a first connecting part 231 and a second connecting part 232, which are respectively connected to the axial ends of the telescopic section 230. The first connecting part 231 and the second connecting part 232 respectively have a fifth connecting hole 40 and a sixth connecting hole 41. The first housing part 21 and the second housing part 22 respectively have a seventh connecting hole 42 and an eighth connecting hole 43. The turbine outer ring connecting structure 100 also includes a third connecting member 44 and a fourth connecting member 45. The third connecting member 44 connects to the fifth connecting hole 40 and the seventh connecting hole 42 to connect the first housing part 21 and the first connecting part 23. The fourth connecting member 45 connects to the sixth connecting hole 41 and the eighth connecting hole 43 to connect the second housing part 22 and the second connecting part 23. This arrangement makes the connection more stable. In some embodiments, such as Figure 2 As shown, the third connector 44 and the fourth connector 45 are bolts.

[0060] refer to Figure 3 As shown, in some embodiments, the specific structure of the telescopic section 230 can be that the telescopic section 230 is corrugated, which is easy to process and manufacture, and has better extensibility, which is conducive to the axial displacement of the central bearing casing and prevents thermal stress caused by thermal mismatch.

[0061] refer to Figure 1 As shown, in some embodiments, the turbine outer ring connection structure 100 may have a specific structure in which the turbine outer ring component 1 is made of ceramic matrix composite material and the intermediate bearing casing 2 is made of high-temperature alloy. The structure of the turbine outer ring component made of ceramic matrix composite material is similar to a π-shape, which is convenient for manufacturing. At the same time, the use of ceramic matrix composite material enables the turbine outer ring component to have excellent properties such as high temperature resistance and high hardness, while reducing the weight of the turbine outer ring component and achieving lightweight design.

[0062] In one embodiment, the specific structure of the gas turbine engine may include the turbine outer ring connection structure as described above. In a gas turbine engine employing the turbine outer ring connection structure described above, the turbine outer ring component of the turbine outer ring connection structure can effectively insulate heat, significantly increasing the turbine inlet temperature and improving engine performance. Simultaneously, while limiting the turbine outer ring component, the turbine outer ring connection structure also allows axial displacement between the intermediate bearing casing and the turbine outer ring component, achieving stress release and eliminating concerns about thermal mismatch stress caused by excessive temperature, leading to component damage.

[0063] refer to Figure 1As shown, in one embodiment, the specific structure of the intermediate support casing 2 may include a first casing portion 21, a second casing portion 22, and a connecting portion 23 located between the two. The connecting portion 23 includes a telescopic section 230, which is detachably connected to the first casing portion 21 and the second casing portion 22 on both axial sides. Dividing the intermediate support casing into multiple sections, compared to the traditional integral intermediate support casing design of a first casing portion, a second casing portion, and a connecting portion between the two, facilitates assembly. The telescopic section can adjust the axial dimension of the intermediate support casing, allowing axial displacement of the intermediate support casing during engine operation and relieving axial stress in the intermediate support casing.

[0064] refer to Figures 1 to 3 As shown, in one embodiment, a connection method for mounting a first annular member to a second annular member coaxial with it, wherein the first annular member is made of a first material and the second annular member is made of a second material, the coefficient of thermal expansion of the first material being less than that of the second material, may include the following steps:

[0065] The first annular component is provided with an axially adjacent first rib and a second rib extending radially outward from the first annular component, each having a first connecting hole and a second connecting hole, respectively. Continuing from the above, the first environmental component is a turbine outer ring component 1, including a turbine outer ring body 11 and an extension 12. The extension 12 includes an axially adjacent first rib 121 and a second rib 122 extending radially outward from the turbine outer ring body 11. The first rib 121 and the second rib 122 each have a first connecting hole 311 and a second connecting hole 32, respectively.

[0066] The second annular component is configured as a separate first part, a second part, and a connecting part located between the two for connecting the two. As described above, the second annular component is a central support housing 2, which includes a separate first housing part 21, a second housing part 22, and a connecting part 23 located between the two.

[0067] The first part is configured to be detachably connected to the first rib, and the second part is configured to be detachably connected to the second rib. The connecting part includes a telescopic section whose axial length is telescopic. The telescopic section is detachably connected to the first part and the second part on both sides of the axial direction, respectively. The coefficient of thermal expansion of the first annular component is less than that of the second annular component. Continuing from the above, the first casing part 21 is detachably connected to the first rib 121, and the second casing part 22 is detachably connected to the second rib 122. The connecting part 23 includes a telescopic section 230, which is detachably connected to the first casing part 21 and the second casing part 22 on both sides of the axial direction, respectively. The coefficient of thermal expansion of the turbine outer ring 1 is less than that of the intermediate bearing casing 2.

[0068] The connection method of this embodiment allows both the first annular component and the second annular component to undergo axial displacement, effectively preventing thermal mismatch stress caused by the difference in thermal expansion coefficients, which could lead to component damage. At the same time, it can also limit the movement of the first annular component.

[0069] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A turbine outer ring connection structure, characterized in that, include: A turbine outer ring component includes a turbine outer ring body and an extension, wherein the extension extends radially outward from the turbine outer ring body and has axially adjacent first and second ribs. The central support casing includes a first casing section, a second casing section, and a connecting section located between the two, which are separately arranged; The first casing portion is detachably connected to the first rib, and the second casing portion is detachably connected to the second rib. The connecting portion includes a telescopic section, which is detachably connected to the first casing portion and the second casing portion on both axial sides, respectively. The coefficient of thermal expansion of the turbine outer ring is less than that of the intermediate bearing casing. The second casing includes a first section and a second section, with an axial space between the first section and the second section. The second rib is located within the axial space, and the axial dimension of the second rib is smaller than the dimension of the axial space.

2. The turbine outer ring connection structure as described in claim 1, characterized in that: The first rib and the second rib respectively have a first connecting hole and a second connecting hole; The first casing portion and the second casing portion of the central support casing each have a third connecting hole corresponding to the first connecting hole and a fourth connecting hole corresponding to the second connecting hole; The turbine outer ring connection structure further includes a first connector and a second connector; The first connector connects the first connecting hole and the third connecting hole. The first rib is tightly connected to the first housing part in an axial plane. The first rib is located on the axial downstream side of the first housing part. An elastic element is provided at the contact position between the first connector and the first rib. The fourth connecting hole includes a first hole segment and a second hole segment. The second connector sequentially connects the first hole segment, the second connecting hole, and the second hole segment of the fourth connecting hole in the axial direction from upstream to downstream.

3. The turbine outer ring connection structure as described in claim 2, characterized in that, The turbine outer ring connection structure includes both cold and hot states: In the cold state, the first casing portion is tightly connected to the first rib, the first section of the second casing portion is tightly connected to the second rib, and the second section of the second casing portion has a first axial gap with the second rib; In the hot state, the first casing portion is tightly connected to the first rib, the first section of the second casing portion is tightly connected to the second rib, and the second section of the second casing portion and the second rib have a second axial gap, which is smaller than the first axial gap.

4. The turbine outer ring connection structure as described in claim 2, characterized in that, The first section of the second casing includes a first body and a first protrusion, and the second section includes a second body and a second protrusion. The first protrusion extends axially downstream from the first body, and the second protrusion extends axially upstream from the second body. The first protrusion and the second protrusion are used to axially limit the second rib.

5. The turbine outer ring connection structure as described in claim 2, characterized in that, The thermal expansion coefficients of the first connector and the second connector are the same as those of the central bearing casing, and the first connector and the second connector are respectively clearance fits with the first connecting hole and the second connecting hole.

6. The turbine outer ring connection structure as described in claim 2, characterized in that, The first connecting hole, the second connecting hole, the third connecting hole, and the fourth connecting hole are arranged coaxially.

7. The turbine outer ring connection structure as described in claim 2, characterized in that, The first segment includes a first body and a first connector; the second segment includes a second body and a second connector; the first connector has a first hole section with the fourth connector hole; the second connector has a second hole section with the fourth connector hole; there is an axial space between the first connector and the second connector; the second rib is located within this axial space, and the axial dimension of the second rib is smaller than the dimension of the axial space; the first body and the second body are detachably and fixedly connected face to face; the first body and the connector are detachably connected.

8. The turbine outer ring connection structure as described in claim 1, characterized in that, The first casing includes a first casing body and a first mounting part. The first mounting part is detachably connected to the first rib. The first casing body has a cold air passage that connects the space defined by the intermediate bearing casing and the turbine outer ring.

9. The turbine outer ring connection structure as described in claim 1, characterized in that, The connecting part further includes a first connecting part and a second connecting part, which are respectively connected to the two ends of the telescopic section. The first connecting part and the second connecting part have a fifth connecting hole and a sixth connecting hole, respectively. The first casing part and the second casing part have a seventh connecting hole and an eighth connecting hole, respectively. The turbine outer ring connecting structure further includes a third connecting member and a fourth connecting member. The third connecting member connects the fifth connecting hole and the seventh connecting hole to connect the first casing part and the first connecting part. The fourth connecting member connects the sixth connecting hole and the eighth connecting hole to connect the second casing part and the second connecting part.

10. The turbine outer ring connection structure as described in claim 1, characterized in that, The expandable section is corrugated.

11. The turbine outer ring connection structure as described in claim 1, characterized in that, The turbine outer ring is made of ceramic matrix composite material, and the intermediate bearing casing is made of high temperature alloy.

12. A gas turbine engine, characterized in that, Includes the turbine outer ring connection structure as described in any one of claims 1-11.

13. A central support casing, characterized in that, The turbine outer ring connection structure as described in any one of claims 1-11 includes a first casing portion, a second casing portion, and a connecting portion located between the two separately disposed; wherein the connecting portion includes a telescopic section, the telescopic section being detachably connected to the first casing portion and the second casing portion on both axial sides respectively.

14. A connection method for mounting a first annular member to a second annular member coaxial therewith, wherein the first annular member is made of a first material, the second annular member is made of a second material, and the coefficient of thermal expansion of the first material is less than the coefficient of thermal expansion of the second material, characterized in that... include: The first annular member is provided with an axially adjacent first rib and a second rib extending radially outward from the first annular member, and the two ribs respectively have a first connection and a second connection hole; The second annular component is configured as a split first part, a second part, and a connecting part located between the two for connecting the two; wherein, the second part includes a first segment and a second segment, there is an axial space between the first segment and the second segment, the second rib is located in the axial space, and the axial dimension of the second rib is smaller than the dimension of the axial space. The first part is configured to be detachably connected to the first rib, and the second part is configured to be detachably connected to the second rib. The connecting part includes a telescopic section whose length in the axial direction is telescopic. The telescopic section is detachably connected to the first part and the second part on both sides in the axial direction, respectively. The coefficient of thermal expansion of the first annular part is less than that of the second annular part.

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