Turbine interstage casing with box-shaped heat shield structure and aero-engine

Abstract

The invention provides a turbine interstage casing with a box-shaped heat shield structure, which comprises an outer casing, an inner casing, a plurality of rectifying blades, a plurality of bearing support plates and a plurality of box-shaped heat shields, the rectifying blades are mounted on the outer casing, the box-shaped heat shields are mounted between the rectifying blades and the outer casing, one end of each bearing support plate is connected with the inner casing, and the other end of each bearing support plate is connected with the box-shaped heat shields. The box-shaped heat insulation covers are located on the two sides of the corresponding force bearing supporting plates. Cold air holes are formed in the two sides of the force bearing supporting plate, so that cooling media flowing out of the cold air holes flow into the box-shaped heat insulation cover, and the box-shaped heat insulation cover, the outer casing and the rectifying blades form a three-layer air layer structure. The interstage case cold air cooling effect is improved, and the risk that the temperature of the outer case of the interstage case and the temperature of the rectifying blades are too high is reduced. And on the basis that the cooling effect is improved, less cold air can be introduced into the interstage casing, the loss of main flow air flow is reduced, and then the efficiency of the engine is optimized.

Description

Technical Field

[0001] The invention relates to the field of aircraft engine turbine structures, and in particular to a turbine interstage casing with a box-shaped heat shield structure and an aircraft engine. Background Art

[0002] In the prior art, the main structure of a commercial aircraft engine generally includes components such as a fan booster stage, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine. Between the high-pressure turbine and the low-pressure turbine is a transition section interstage casing. The main components of the interstage casing include an outer casing, an inner casing, a load-bearing support plate, and a straightening blade. The outer casing, the load-bearing support plate, and the inner casing form a load-bearing frame.

[0003] The straightening blades isolate the gas from the flow path to ensure that the load-bearing frame works at a safe temperature. In order to cool the load-bearing frame and reduce the temperature of the bearing seat oil pipe and the gas pipe, the cold air introduced from the high-pressure compressor enters the cavity of the load-bearing support plate and the inner casing from the outer casing, and then enters the straightening blades and the outer cavity of the outer casing through the holes on the support plate, cooling the outer casing and the straightening blades.

[0004] The hottest part of the interstage casing when the engine is in operation is the straightening blades, which generally operate at temperatures exceeding 1000 K. Due to direct heat conduction, the outer casing connection where the straightening blades are fixed is usually at risk of critical overtemperature.

[0005] At the same time, the various mounting seats and sealing rings on the outside of the outer casing also need to avoid overheating during operation to ensure structural strength and sealing effect. Therefore, cooling measures are required for the outer casing structure to reduce the temperature of itself and the surface mounting seats.

[0006] There is a solution that installs a heat shield structure in the cavity between the straightening blades and the outer casing to reduce the heat radiation of the straightening blades to the outer casing and thus reduce the temperature of the outer casing.

[0007] Aircraft engines are developing towards higher fuel efficiency, greater thrust-to-weight ratio and longer service life, which requires higher gas temperature. The interstage casing at the high-pressure turbine outlet, as a load-bearing frame, faces the risk of over-temperature. To reduce the risks of decreased structural strength and rigidity, weakened sealing effect, etc. caused by over-temperature, when using the original high-temperature alloy material (IN718), it is necessary to utilize the space between the rectifier blades and the casing to optimize the cooling effect, which can improve the rigidity and stability of the load-bearing frame parts.

[0008] In view of this, the inventor of the present application has designed a turbine interstage casing and an aircraft engine with a box-shaped heat shield structure, in order to overcome the above-mentioned technical problems. Summary of the invention

[0009] The technical problem to be solved by the present invention is to overcome the defects in the prior art that the outer casing connection of the straightening blades usually faces the risk of critical overheating, and to provide a turbine interstage casing and an aircraft engine with a box-shaped heat shield structure.

[0010] The present invention solves the above technical problems through the following technical solutions:

[0011] The present invention provides a turbine interstage casing with a box-shaped heat shield structure, which is characterized in that the turbine interstage casing comprises an outer casing, an inner casing, a plurality of straightening blades, a plurality of load-bearing support plates and a plurality of box-shaped heat shields, the straightening blades are mounted on the outer casing, and the box-shaped heat shields are mounted between the straightening blades and the outer casing, one end of the load-bearing support plate is connected to the inner casing, and the other end passes through the outer casing, and the box-shaped heat shields are located on both sides corresponding to the load-bearing support plates;

[0012] Cooling holes are provided on both sides of the load-bearing support plate, so that the cooling medium flowing out of the cooling holes flows into the box-shaped heat insulation cover, and the box-shaped heat insulation cover, the outer casing and the straightening blades form a three-layer air layer structure.

[0013] According to one embodiment of the present invention, the box-shaped heat insulation cover comprises an upper heat insulation layer, a lower heat insulation layer, a left connecting section and a right connecting section, and the left connecting section and the right connecting section are respectively connected between the two side ends of the upper heat insulation layer and the lower heat insulation layer to form a hollow cavity structure.

[0014] According to one embodiment of the present invention, the upper heat insulation layer is provided with a plurality of upper air guide grooves, and the lower heat insulation layer is provided with a plurality of lower air guide grooves, and the upper air guide grooves and the lower air guide grooves are inwardly concave grooves.

[0015] According to an embodiment of the present invention, the cold air holes of the load-bearing support plate correspond to the upper air inlet groove and the lower air inlet groove of the box-shaped heat insulation cover respectively.

[0016] According to one embodiment of the present invention, the distance between the upper heat insulation layer and the outer casing is 2 mm to 4 mm, and the distance between the lower heat insulation layer and the straightening blade is 4 mm to 8 mm.

[0017] According to one embodiment of the present invention, two cooling air holes are respectively arranged on both sides of the load-bearing support plate, and the cooling air holes include upper cooling air holes and lower cooling air holes, the upper cooling air holes correspond to the upper air intake grooves, and the lower cooling air holes correspond to the lower air intake grooves.

[0018] According to an embodiment of the present invention, a first through hole is formed in the upper heat insulation layer, and a second through hole is formed in the lower heat insulation layer. The first through hole and the second through hole correspond to each other vertically and pass through the box-shaped heat insulation cover.

[0019] According to one embodiment of the present invention, each of the box-shaped heat shields is mounted to the outer casing by a plurality of sets of fasteners.

[0020] According to an embodiment of the present invention, a straightening blade bolt groove is provided on one side of the box-shaped heat shield for connecting the straightening blade.

[0021] The present invention also provides an aircraft engine, which is characterized in that the aircraft engine includes a turbine interstage casing with a box-shaped heat shield structure as described above.

[0022] The positive and progressive effects of the present invention are:

[0023] Compared with a structure that does not use a heat shield or uses only one layer of heat shield, the turbine interstage casing and the aircraft engine with a box-shaped heat shield structure of the present invention improve the cooling effect of the interstage casing cold air and reduce the risk of excessive temperature of the outer casing and the straightening blades of the interstage casing. On the basis of improving the cooling effect, less cold air can be introduced at the interstage casing, reducing the loss of mainstream airflow, thereby optimizing the efficiency of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features, wherein:

[0025] Figure 1 It is a schematic structural diagram of a turbine interstage casing with a box-shaped heat shield structure according to the present invention.

[0026] Figure 2 It is a three-dimensional view of a turbine interstage casing with a box-shaped heat shield structure according to the present invention.

[0027] Figure 3 It is a schematic structural diagram of a box-shaped heat shield in a turbine interstage casing with a box-shaped heat shield structure according to the present invention.

[0028] Figure 4 The figure is a top view of a box-shaped heat shield in a turbine interstage casing with a box-shaped heat shield structure according to the present invention.

[0029] Figure 5 The present invention is a schematic structural diagram of a load-bearing support plate in a turbine interstage casing with a box-shaped heat shield structure.

[0030] Figure 6 It is a schematic diagram of the airflow in the load-bearing support plate of the turbine interstage casing with the box-shaped heat shield structure of the present invention entering the heat shield.

[0031] [Reference Signs]

[0032] Outer Receiver 10

[0033] Inner Receiver 20

[0034] Straightening blade 30

[0035] Load bearing plate 40

[0036] Box-shaped heat shield 50

[0037] Upper insulation layer 51

[0038] Lower insulation layer 52

[0039] Left connecting section 53

[0040] Right connecting section 54

[0041] Upper air duct 511

[0042] Lower air duct 521

[0043] First through hole 512

[0044] The second through hole 522

[0045] Straightening blade bolt slot 55

[0046] Connection hole 56

[0047] Upper air vent 41

[0048] Lower air vent 42

[0049] Fastener 60

[0050] Air conditioning pipe 70

[0051] Bearing seat 80

[0052] Bearing 81

[0053] Rear hook 90 DETAILED DESCRIPTION

[0054] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0055] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to preferred embodiments of the present invention, examples of which are shown in the accompanying drawings. Wherever possible, the same reference numerals will be used throughout the drawings to represent the same or similar parts.

[0056] Furthermore, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the present invention specification may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this document.

[0057] Furthermore, it is required that the present invention be understood not only by the actual terms used but also by the meanings connoted by each term.

[0058] like Figure 1 and Figure 2 As shown, the present invention discloses a turbine interstage casing with a box-shaped heat shield structure. The turbine interstage casing refers to a component located between the high-pressure turbine and the low-pressure turbine in an aircraft engine, which guides the high-pressure turbine outlet gas to transition to the low-pressure turbine inlet and fixes the engine bearing. The turbine interstage casing includes an outer casing 10, an inner casing 20, a plurality of straightening blades 30 (parts in the interstage casing used to form a flow channel cavity and guide the gas from the high-pressure turbine outlet to the low-pressure turbine inlet), a plurality of bearing support plates 40 and a plurality of box-shaped heat shields 50.

[0059] Among them, the straightening blade 30 is installed on the outer casing 10, and the box-shaped heat shield 50 is installed between the straightening blade 30 and the outer casing 10. One end of the load-bearing support plate 40 is connected to one end of the inner casing 20, and the other end passes through the outer casing 10, so that the box-shaped heat shield 50 is located on both sides of the corresponding load-bearing support plate 40. At the same time, the outlet of the cold air pipe 70 is connected to the other end of the load-bearing support plate 40. A bearing seat 80 and a bearing 81 are installed at the other end of the inner casing 20. A rear hook 90 is also installed at the rear of the box-shaped heat shield 50.

[0060] Cooling holes are provided on both sides of the load-bearing support plate 40, so that the cooling medium flowing out of the cooling holes flows into the box-shaped heat insulation cover 50, and the box-shaped heat insulation cover 50, the outer casing 10, and the straightening blades 30 form a three-layer air layer structure (such as Figure 3 For example, when the interstage casing in this embodiment uses 12 straightening blades, 12 box-shaped heat shields are installed accordingly.

[0061] like Figure 3 and Figure 4 As shown, in this embodiment, the box-shaped heat insulation cover 50 preferably includes an upper heat insulation layer 51, a lower heat insulation layer 52, a left connecting section 53 and a right connecting section 54, and the left connecting section 53 and the right connecting section 54 are respectively connected between the two side ends of the upper heat insulation layer 51 and the lower heat insulation layer 52 to form a hollow cavity structure.

[0062] Preferably, the upper insulation layer 51 is provided with a plurality of upper air guide grooves 511, and the lower insulation layer 52 is provided with a plurality of lower air guide grooves 521, and the upper air guide grooves 511 and the lower air guide grooves 521 are preferably provided as inwardly concave grooves. The upper air guide grooves 511 and the lower air guide grooves 521 are used to guide the cold air from the load-bearing support plate 40.

[0063] The distance between the upper heat insulation layer 51 and the outer casing 10 is preferably 2 mm to 4 mm, and the distance between the lower heat insulation layer 52 and the rectifying blades 30 is preferably 4 mm to 8 mm.

[0064] Furthermore, a first through hole 512 is formed on the upper heat insulation layer 51 , and a second through hole 522 is formed on the lower heat insulation layer 52 , so that the first through hole 512 and the second through hole 522 correspond to each other up and down and pass through the box-shaped heat insulation cover.

[0065] In addition, a straightening blade bolt groove 55 is provided on one side of the box-shaped heat shield 50 for connecting the straightening blade 30 .

[0066] like Figure 5 As shown, two cooling holes are respectively arranged on both sides of the load-bearing support plate 40, and the cooling holes include an upper cooling hole 41 and a lower cooling hole 42, so that the upper cooling hole 41 corresponds to the upper air inlet groove 511, and the lower cooling hole 42 corresponds to the lower air inlet groove 521. In this way, the cooling holes of the load-bearing support plate 40 can correspond to the upper air inlet groove 511 and the lower air inlet groove 521 of the box-shaped heat insulation cover 50.

[0067] The cold air coming out of the load-bearing support plate 40 enters between the straightening blade 30 and the box-shaped heat insulation cover 50, and between the outer casing 10 and the box-shaped heat insulation cover 50, respectively, and passes through the lower cold air holes 42 corresponding to the lower air guide grooves 521 to cool the straightening blade 30 or the outer casing 10, and guide part of the cold air to the connection position of the straightening blade 30 and the outer casing 10.

[0068] The turbine interstage casing with the box-shaped heat shield structure determines whether the cooling air is used to cool the straightening blades 30 first, or to cool the wall surface of the outer casing 10 and the connection structure of the outer casing 10 by controlling the diameter of the upper cooling air holes 41 and the diameter of the lower cooling air holes 42.

[0069] The judgment basis of this method is: depending on whether there is an over-temperature risk on the rectifying blade 30 or the outer casing 10, when the rectifying blade 30 has an over-temperature problem, the aperture ΦB of the lower cooling air hole 42 in the structure should be larger than the aperture ΦA of the upper cooling air hole 41, or the upper cooling air hole 41 can be eliminated, so that the cold air is preferentially guided to the lower layer of the heat insulation cover, that is, between the rectifying blade 30 and the lower insulation layer 52.

[0070] When the rectifying blades 30 are not overheated, but the outer casing 10 and the outer casing connection are at risk of overheating, the aperture ΦA of the upper cooling air hole 41 should be larger than the aperture ΦB of the lower cooling air hole 42, and more cooling air will be distributed to the upper and lower layers of the heat insulation cover. Part of the cooling air will be guided by the heat insulation cover to the outer casing and the connection between the outer casing and the rectifying blades, thereby reducing the temperature of the connection.

[0071] like Figure 2 As shown, in order to prevent the heat shield from vibrating under the action of cold air, each box-shaped heat shield 50 is provided with a plurality of connection holes 56, and is mounted on the outer casing 10 through a plurality of sets of fasteners 60. For example, each heat shield is mounted on the outer casing 10 through three or four sets of fasteners 60. The connection structure (fasteners 60) here may include bolts, support plate nuts, washers and other parts.

[0072] The present invention also provides an aircraft engine, which includes a turbine interstage casing with a box-shaped heat shield structure as described above.

[0073] In the turbine interstage casing with a box-shaped heat shield structure of the present invention, the box-shaped heat shield structure includes two upper and lower heat shield layers, two left and right connecting sections, and four sections form a box-shaped structure. The two layers of heat shields, the outer casing, and the straightening blades form a three-layer cavity, the lower layer is close to the straightening blades, and the lower layer of heat shield has air guide grooves to guide the cold air from the holes of the load-bearing support plate into between the straightening blades and the heat shield. On the one hand, it cools the blades and reduces heat radiation. The upper layer of heat shield is attached to the outer casing to further reduce the radiation of the straightening blades. On the other hand, the lower layer of heat shield guides the gas to seal the straightening blades to avoid the problem of gas backflow.

[0074] In summary, the turbine interstage casing and aircraft engine with a box-shaped heat shield structure of the present invention improve the cooling effect of the interstage casing cold air, and reduce the risk of excessive temperature of the outer casing and the straightening blades of the interstage casing, compared with the structure without a heat shield or with only one layer of heat shield. On the basis of improving the cooling effect, less cold air can be introduced at the interstage casing, reducing the loss of mainstream airflow, thereby optimizing the efficiency of the engine.

[0075] The turbine interstage casing and aircraft engine with a box-shaped heat shield structure of the present invention improve the cooling effect of the interstage casing, reduce the risk of overheating of the outer casing of the interstage casing, reduce the vibration of the heat shield by the fixed structure, and simultaneously reduce the loss of airflow, optimize the efficiency of the engine, and have high practical value.

[0076] For those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary implementation of the present application.

[0077] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0078] Although the specific embodiments of the present invention are described above, it should be understood by those skilled in the art that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. A turbine interstage casing with a box-shaped heat shield structure, characterized in that: The turbine interstage casing comprises an outer casing, an inner casing, a plurality of straightening blades, a plurality of load-bearing support plates and a plurality of box-shaped heat shields, wherein the straightening blades are mounted on the outer casing, and the box-shaped heat shields are mounted between the straightening blades and the outer casing, one end of the load-bearing support plate is connected to the inner casing, and the other end passes through the outer casing, and the box-shaped heat shields are located on both sides of the corresponding load-bearing support plates; Cooling holes are provided on both sides of the load-bearing support plate, so that the cooling medium flowing out of the cooling holes flows into the box-shaped heat insulation cover, and the box-shaped heat insulation cover, the outer casing and the straightening blades form a three-layer air layer structure.

2. The turbine interstage casing with a box-shaped heat shield structure according to claim 1, characterized in that: The box-shaped heat insulation cover comprises an upper heat insulation layer, a lower heat insulation layer, a left connecting section and a right connecting section. The left connecting section and the right connecting section are respectively connected between the two side ends of the upper heat insulation layer and the lower heat insulation layer to form a hollow cavity structure.

3. The turbine interstage casing with a box-shaped heat shield structure according to claim 2, characterized in that: The upper heat insulation layer is provided with a plurality of upper air guide grooves, and the lower heat insulation layer is provided with a plurality of lower air guide grooves, and the upper air guide grooves and the lower air guide grooves are inwardly concave grooves.

4. The turbine interstage casing with a box-shaped heat shield structure according to claim 3, characterized in that: The cold air holes of the load-bearing support plate correspond to the upper air inlet groove and the lower air inlet groove of the box-shaped heat insulation cover respectively.

5. The turbine interstage casing with a box-shaped heat shield structure according to claim 2, characterized in that: The distance between the upper heat insulation layer and the outer casing is 2 mm to 4 mm, and the distance between the lower heat insulation layer and the straightening blade is 4 mm to 8 mm.

6. The turbine interstage casing with a box-shaped heat shield structure according to claim 3, characterized in that: Two cooling air holes are respectively arranged on both sides of the load-bearing support plate, and the cooling air holes include upper cooling air holes and lower cooling air holes. The upper cooling air holes correspond to the upper air intake grooves, and the lower cooling air holes correspond to the lower air intake grooves.

7. The turbine interstage casing with a box-shaped heat shield structure according to claim 2, characterized in that: The upper heat insulation layer is provided with a first through hole, and the lower heat insulation layer is provided with a second through hole. The first through hole and the second through hole correspond to each other vertically and penetrate the box-shaped heat insulation cover.

8. The turbine interstage casing with a box-shaped heat shield structure according to claim 2, characterized in that: Each of the box-shaped heat shields is mounted on the outer casing by a plurality of sets of fasteners.

9. The turbine interstage casing with a box-shaped heat shield structure according to claim 2, characterized in that: A straightening blade bolt groove is provided on one side of the box-shaped heat insulation cover for connecting the straightening blade.

10. An aircraft engine, characterized in that: The aircraft engine comprises a turbine interstage casing with a box-shaped heat shield structure as described in any one of claims 1 to 9.

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