Turbine containment casing structure and aeroengine

Abstract

This invention relates to the field of aero-engine technology, and discloses a turbine enclosure casing structure and an aero-engine. The turbine enclosure casing structure includes a force transmission casing and an enclosure casing, with the enclosure casing disposed on the force transmission casing. The enclosure casing has a first alloy layer and a second alloy layer made of high-temperature stainless steel. The first alloy layer has an air inlet and a first annular groove communicating with the air inlet. The second alloy layer has a second annular groove. The first and second annular grooves combine to form an annular cavity, allowing cool air to enter the annular cavity from the air inlet and distribute the cool air evenly throughout the casing. The high-temperature stainless steel material has a low density, and combined with the first and second alloy layers to form an upper and lower two-layer structure, it achieves the effects of light weight and good enclosure performance, improving the engine's power-to-weight ratio. The turbine enclosure casing structure provided by this invention solves the problem of excessive turbine casing weight in the prior art, which affects the engine's power-to-weight ratio.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a turbine housing structure and an aero-engine. Background Technology

[0002] The turbine casing is one of the most important components of an aircraft engine. It not only provides an airflow passage but also contains blade fragments when the turbine blades break, preventing damage to the aircraft and making it crucial for flight safety.

[0003] In the prior art, the turbine casing is in a high-temperature environment, with the turbine casing temperature exceeding 300-400 degrees Celsius. In order to achieve the effect of containing blade fragments, the turbine casing structure usually adopts a thicker high-temperature alloy shell to ensure sufficient strength and consume the kinetic energy of the blade fragments.

[0004] However, the high density and thickness of the high-temperature alloy turbine casing result in a large weight of the turbine casing, which affects the power-to-weight ratio of the engine. In addition, the high price of high-temperature alloy raw materials and the difficulty of processing them lead to increased costs. Summary of the Invention

[0005] This invention provides a turbine housing structure and an aero-engine to solve the problem of excessive turbine housing weight affecting the engine power-to-weight ratio in the prior art.

[0006] In a first aspect, the present invention provides a turbine containment casing structure, including a power transmission casing and a containment casing, wherein the containment casing is disposed on the power transmission casing, and the containment casing has a first alloy layer and a second alloy layer made of high-temperature stainless steel. The first alloy layer is disposed on the second alloy layer, and the first alloy layer has an air inlet. A first annular groove communicating with the air inlet is provided on the side of the first alloy layer near the second alloy layer, and a second annular groove opposite to the first annular groove is provided on the second alloy layer. The first annular groove and the second annular groove are combined to form an annular cavity, and the annular cavity is used to uniformly distribute cold air.

[0007] Beneficial effects: The enclosed casing is mounted on the force transmission casing, which transmits force to the connecting casing. Cool air enters the annular cavity from the air inlet and is evenly distributed throughout the casing. The high-temperature stainless steel material has a low density, and combined with the first and second alloy layers to form a two-layer structure, it is lightweight and has good enclosed performance, which is beneficial to improving the engine's power-to-weight ratio. The turbine enclosed casing structure provided by this invention solves the problem of excessive turbine casing weight in the prior art, which affects the engine's power-to-weight ratio.

[0008] In one optional embodiment, a hollow layer is provided between the containment casing and the force transmission casing, and the hollow layer communicates with the annular cavity.

[0009] Beneficial effect: The cold air inside the annular cavity enters the hollow layer, which can reduce the temperature on the outside of the force transmission casing, thereby reducing the heat radiation of the force transmission casing to the outside.

[0010] In one optional embodiment, the second alloy layer is provided with a plurality of inclined holes, one end of the inclined holes being connected to the second annular groove, and the other end of the inclined holes being connected to the hollow layer.

[0011] Beneficial effects: By uniformly injecting cold air into the force transmission casing through the inclined holes, the temperature of the force transmission casing can be reduced. At the same time, a cold air jet is formed in the hollow layer between the force transmission casing and the containment casing, which further reduces the temperature of the outer side of the force transmission casing and reduces the heat radiation of the force transmission casing to the outside.

[0012] In one alternative implementation, the force transmission housing and the containment housing are connected by fasteners.

[0013] Beneficial effects: By fastening the enclosure casing to the force transmission casing, the contact area between the enclosure casing and the force transmission casing can be reduced, heat transfer can be suppressed, the impact of high temperature on the enclosure casing can be reduced, and the enclosure performance of the enclosure casing can be improved.

[0014] In one optional embodiment, the force transmission housing is provided with a mounting boss, the mounting boss is provided with a first mounting hole, the first mounting hole is a threaded hole, the fastener is a bolt, the housing is provided with a second mounting hole through which the fastener passes, and the fastener is threadedly connected to the first mounting hole.

[0015] Beneficial effects: The first mounting hole on the mounting boss is a threaded hole, which makes it easy to install the enclosure casing on the force transmission casing with bolts. This facilitates installation and reduces the contact area between the force transmission casing and the enclosure casing, thus suppressing heat transfer.

[0016] In one alternative embodiment, several mounting bosses are evenly distributed circumferentially in the middle part of the force transmission casing.

[0017] Beneficial effect: The several mounting bosses evenly distributed in the middle part of the force transmission casing can improve the stability of the housing casing when installed on the force transmission casing.

[0018] In one alternative embodiment, a turbine ring is also provided on the side of the power transmission casing near the turbine.

[0019] Beneficial effects: A gas passage is formed between the turbine ring and the turbine blades, which converts the internal energy of the gas into the kinetic energy of the rotor and outputs power. At the same time, it effectively isolates the heat radiation of the gas to the power transmission casing, further reducing the impact of the high temperature of the gas on the casing.

[0020] In one alternative embodiment, the power transmission casing and the turbine ring are made of high-temperature alloy.

[0021] Beneficial effects: The power transmission casing and turbine ring made of high-temperature alloy can meet the usage requirements of high-temperature gas environments.

[0022] In one alternative embodiment, the inner side of the turbine ring is provided with a wear-resistant coating.

[0023] Beneficial effects: The wear-resistant coating on the inside of the turbine ring can extend the service life of the turbine ring.

[0024] In a second aspect, the present invention also provides an aircraft engine, comprising: a turbine and a turbine housing structure as described in the above embodiments, wherein the turbine is disposed inside the turbine housing structure.

[0025] Beneficial effects: The turbine housing structure is lightweight and has good containment performance, which can improve the power-to-weight ratio of the aero engine; at the same time, it can effectively suppress the heat radiation of the housing to the aircraft engine compartment. Attached Figure Description

[0026] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of a turbine enclosure casing according to an embodiment of the present invention;

[0028] Figure 2 for Figure 1 A partial cross-sectional schematic diagram of the turbine enclosure casing.

[0029] Explanation of reference numerals in the attached figures: 1. Power transmission casing; 2. Enclosure casing; 3. First alloy layer; 4. Second alloy layer; 5. Air inlet; 6. Annular cavity; 7. Hollow layer; 8. Inclined hole; 9. Fastener; 10. Mounting boss; 11. Turbine ring. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] The following is combined with Figures 1 to 2 The following describes embodiments of the present invention.

[0032] According to an embodiment of the present invention, a turbine enclosure casing structure is provided, including a power transmission casing 1 and an enclosure casing 2. The enclosure casing 2 is disposed on the power transmission casing 1. The enclosure casing 2 has a first alloy layer 3 and a second alloy layer 4 made of high-temperature stainless steel. The first alloy layer 3 is disposed on the second alloy layer 4. The first alloy layer 3 has an air inlet 5. A first annular groove communicating with the air inlet 5 is provided on the side of the first alloy layer 3 near the second alloy layer 4. A second annular groove opposite to the first annular groove is provided on the second alloy layer 4. The first annular groove and the second annular groove combine to form an annular cavity 6. The annular cavity 6 is used to uniformly distribute cold air.

[0033] The enclosed casing 2 is mounted on the force transmission casing 1, and the force is transmitted to the connecting casing through the force transmission casing 1. Cool air enters the annular cavity 6 from the air inlet 5, and the annular cavity 6 distributes the cool air evenly throughout the casing. The high-temperature stainless steel material has a low density, and together with the first alloy layer 3 and the second alloy layer 4, it forms an upper and lower two-layer structure, which has the effects of light weight and good enclosed performance, which is beneficial to improving the power-to-weight ratio of the engine. The turbine enclosed casing structure provided in this embodiment solves the problem of excessive turbine casing weight in the prior art, which affects the power-to-weight ratio of the engine.

[0034] In one embodiment, a hollow layer 7 is provided between the containment casing 2 and the force transmission casing 1, and the hollow layer 7 communicates with the annular cavity 6. The cold air in the annular cavity 6 enters the hollow layer 7, which can reduce the temperature on the outside of the force transmission casing 1, thereby reducing the heat radiation of the force transmission casing 1 and minimizing the impact of high-temperature combustion gas on the containment casing 2. Alternatively, as an alternative embodiment, the hollow layer 7 between the containment casing 2 and the force transmission casing 1 may not communicate with the annular cavity 6.

[0035] Specifically, the force transmission casing 1 is an annular component with a wall thickness of 2-5mm, used to install the guide, exhaust frame, turbine ring 11 and enclosing casing 2, and to transmit force to the connecting casing.

[0036] In one embodiment, the second alloy layer 4 is provided with a plurality of inclined holes 8, one end of each inclined hole 8 connecting to the second annular groove, and the other end connecting to the hollow layer 7. By uniformly injecting cold air into the force transmission casing 1 through the inclined holes 8, the temperature of the force transmission casing 1 can be reduced. Simultaneously, a cold air jet is formed in the hollow layer 7 between the force transmission casing 1 and the enclosing casing 2, further reducing the outer temperature of the force transmission casing 1 and reducing its external heat radiation. Alternatively, as an alternative embodiment, the inclined holes 8 can be omitted, and the hollow layer 7 and the annular cavity 6 are connected through a vertical hole.

[0037] Specifically, 2-3 rows of evenly distributed inclined holes 8 are machined on the second alloy layer 4.

[0038] In one embodiment, the force transmission housing 1 and the containment housing 2 are connected by fasteners 9. Mounting the containment housing 2 onto the force transmission housing 1 using fasteners 9 reduces the contact area between the containment housing 2 and the force transmission housing 1, suppresses heat transfer, reduces the impact of high temperatures on the containment housing 2, and improves the containment capacity of the containment housing 2. Alternatively, as an alternative implementation, the containment housing 2 and the fasteners 9 can also be connected by flanges or other fixed methods.

[0039] In one embodiment, the force transmission housing 1 is provided with a mounting boss 10, and the mounting boss 10 is provided with a first mounting hole, which is a threaded hole. The fastener 9 is a bolt. The housing 2 is provided with a second mounting hole through which the fastener 9 passes, and the fastener 9 is threadedly connected to the first mounting hole. The first mounting hole on the mounting boss 10 is a threaded hole, which facilitates the installation of the housing 2 onto the force transmission housing 1 by bolting, making installation convenient and reducing the contact area between the force transmission housing 1 and the housing 2, thus suppressing heat transfer. Alternatively, as an alternative embodiment, the second mounting hole can also be a threaded hole.

[0040] In one embodiment, a plurality of mounting bosses 10 are evenly distributed circumferentially along the middle portion of the force transmission housing 1. The evenly distributed mounting bosses 10 along the middle portion of the force transmission housing 1 improve the stability of the housing 2 when mounted on the force transmission housing 1. Alternatively, as an alternative embodiment, the mounting bosses 10 may also be located at both ends of the force transmission housing 1.

[0041] Specifically, the force transmission housing 1 has 6-16 mounting bosses 10 evenly designed in the middle part, and the housing 2 is mounted on the force transmission housing 1 by 6-16 evenly distributed bolts.

[0042] In one embodiment, a turbine ring 11 is also provided on the side of the power transmission casing 1 near the turbine. The turbine ring 11 forms a gas passage with the turbine blades, converting the internal energy of the gas into the kinetic energy of the rotor and outputting power, while effectively isolating the heat radiation of the gas to the power transmission casing 1, further reducing the impact of the high temperature of the gas on the enclosure casing 2.

[0043] Specifically, the turbine ring 11 is a thin-walled annular component with a wall thickness of 2-5mm.

[0044] In one embodiment, the power transmission casing 1 and the turbine ring 11 are made of high-temperature alloy. The power transmission casing 1 and the turbine ring 11 made of high-temperature alloy can meet the requirements for use in high-temperature gas environments.

[0045] In one embodiment, a wear-resistant coating is provided on the inner side of the turbine ring 11. The wear-resistant coating on the inner side of the turbine ring 11 can extend the service life of the turbine ring 11.

[0046] According to an embodiment of the present invention, another aspect provides an aero-engine, comprising: a turbine and a turbine enclosure casing structure as described in the above embodiments, wherein the turbine is disposed inside the turbine enclosure casing structure. The turbine enclosure casing structure has the advantages of being lightweight and having good containment performance, thereby improving the power-to-weight ratio of the aero-engine; at the same time, it can effectively suppress heat radiation from the casing to the aircraft's engine compartment.

[0047] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A turbine enclosure casing structure, characterized in that, include: Power transmission casing (1); An enclosed casing (2) is disposed on the force transmission casing (1). The enclosed casing (2) has a first alloy layer (3) and a second alloy layer (4) made of high-temperature stainless steel. The first alloy layer (3) is disposed on the second alloy layer (4). The first alloy layer (3) has an air inlet (5). The first alloy layer (3) has a first annular groove communicating with the air inlet (5) on one side near the second alloy layer (4). The second alloy layer (4) has a second annular groove opposite to the first annular groove. The first annular groove and the second annular groove are combined to form an annular cavity (6). The annular cavity (6) is used to distribute cold air evenly.

2. The turbine enclosure casing structure according to claim 1, characterized in that, A hollow layer (7) is provided between the enclosing casing (2) and the force transmission casing (1), and the hollow layer (7) is connected to the annular cavity (6).

3. The turbine enclosure casing structure according to claim 2, characterized in that, The second alloy layer (4) is provided with a plurality of inclined holes (8), one end of the inclined hole (8) is connected to the second annular groove, and the other end of the inclined hole (8) is connected to the hollow layer (7).

4. The turbine enclosure casing structure according to claim 2, characterized in that, The force transmission casing (1) and the containment casing (2) are connected by fasteners (9).

5. The turbine enclosure casing structure according to claim 4, characterized in that, The power transmission housing (1) is provided with a mounting boss (10), the mounting boss (10) is provided with a first mounting hole, the first mounting hole is a threaded hole, the fastener (9) is a bolt, the housing (2) is provided with a second mounting hole through which the fastener (9) passes, and the fastener (9) is threadedly connected to the first mounting hole.

6. The turbine enclosure casing structure according to claim 5, characterized in that, The mounting bosses (10) are evenly arranged in the circumferential direction at the middle part of the force transmission casing (1).

7. The turbine enclosure casing structure according to any one of claims 1 to 6, characterized in that, The power transmission casing (1) is also provided with a turbine ring (11) on the side near the turbine.

8. The turbine enclosure casing structure according to claim 7, characterized in that, The power transmission casing (1) and the turbine ring (11) are made of high-temperature alloy.

9. The turbine enclosure casing structure according to claim 7, characterized in that, The inner side of the turbine ring (11) is provided with a wear-resistant coating.

10. An aircraft engine, characterized in that, The invention includes a turbine and a turbine housing structure as described in any one of claims 1-9, wherein the turbine is disposed inside the turbine housing structure.

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