Turbine rotor over-rotation protection device, turbine and aero-engine

Abstract

The invention relates to a turbine rotor over-rotation protection device, a turbine and an aero-engine, belongs to the technical field of aerospace, and solves the problem that a rotor is damaged by a turbine rotor over-rotation protection device in the prior art. The turbine rotor over-rotation protection device comprises a guide vane unit, a first flow channel and a second flow channel, wherein the first flow channel and the second flow channel are used for guiding flow of high-temperature fuel gas; the guide vane unit comprises guide vanes, and the guide vanes are used for rectifying fuel gas for driving the turbine rotor to rotate; the first flow channel is communicated with the guide vane; one end of the second runner communicates with the first runner, and the other end of the second runner communicates with the outside; and when the turbine rotor reaches a preset rotating speed, the guide vane closes the first flow channel and opens the second flow channel. According to the invention, the rotor is not damaged, and the integrity of the rotor is ensured.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, and in particular to a turbine rotor over-speed protection device, a turbine and an aero-engine. BACKGROUND

[0002] The turbine rotor is one of the core components of the aero-engine. The turbine rotor may over-speed (i.e., rotate beyond a predetermined rotational speed) due to sudden increase in fuel quantity caused by malfunction of the fuel regulator, accidental intake of fuel by the compressor, turbine shaft failure and other reasons. When over-speeding, the rotor may break, and under the action of a huge centrifugal force, high-energy rotor fragments may hit the casing, even penetrate the aircraft fuel tank, cut off the aircraft control system and fly into the passenger cabin, thereby seriously endangering flight safety.

[0003] Currently, the over-speed protection method for the turbine rotor mainly destroys the rotor blades or other components of the rotor to achieve rotor speed reduction, but the detached blades and other rotor fragments may damage more components, or cause rotor jamming due to imbalance, and even damage, which brings immeasurable loss to the engine. SUMMARY

[0004] In view of the above analysis, the embodiments of the present application aim to provide a turbine rotor over-speed protection device, a turbine and an aero-engine to solve the problem that the over-speed protection method for the turbine rotor in the prior art causes damage to other components and the rotor itself.

[0005] The main purpose of the present application is achieved by the following technical solutions:

[0006] In a first aspect, the present application provides a turbine rotor over-speed protection device, comprising a guide vane unit, and a first flow channel and a second flow channel for guiding high-temperature gas flow;

[0007] The guide vane unit comprises guide vanes for rectifying the gas driving the turbine rotor to rotate; the first flow channel is in communication with the guide vanes;

[0008] When the turbine rotor reaches a predetermined rotational speed, the guide vanes close the first flow channel, and the second flow channel is opened;

[0009] When the second flow channel is opened, one end of the second flow channel is in communication with the first flow channel, and the other end of the second flow channel is in communication with the outside.

[0010] Further, the guide vane unit further comprises a guide vane outer ring coaxially arranged with the engine; a first air bleed hole is circumferentially arranged on the side wall of the guide vane outer ring.

[0011] Further, an air bleed unit is further included; the air bleed unit comprises an air bleed ring; the air bleed ring is arranged outside the guide vane outer ring, and the air bleed ring can cover the first air bleed hole.

[0012] Further, the outer wall of the outer ring of the guide vane extends to a platform on one side; the bleed ring can move on one side of the platform, abutting the platform or having a gap.

[0013] Further, the end face of the bleed ring near the platform is a first end face, and the end face of the platform is a second end face; when the bleed ring abuts the platform, the first end face and the second end face are fitted.

[0014] Further, the inner casing of the turbine is arranged outside the outer ring of the guide vane, and the end of the inner casing is connected with the outer wall of the inter-turbine support;

[0015] The outer wall of the inter-turbine support, the outer ring of the guide vane, the bleed ring, and the inner casing form a second cavity;

[0016] The wall surface of the inner casing is circumferentially provided with a second bleed hole;

[0017] The outer casing of the turbine is arranged outside the inner casing; the outer casing and the inner casing form a third cavity; and the third cavity is in communication with the outside;

[0018] The bleed ring moves to the side away from the platform, so that the first end face and the second end face have a gap; the first bleed hole, the gap, the second cavity, the second bleed hole, and the third cavity form a second flow channel;

[0019] The bleed ring moves to the side close to the platform, so that the first end face and the second end face are fitted; and the second flow channel is closed.

[0020] Further, the guide vane unit further comprises a guide vane inner ring coaxially arranged with the engine; and the two ends of the guide vane are arranged on the guide vane inner ring and the guide vane outer ring, respectively;

[0021] The guide vanes are arranged in multiple; the multiple guide vanes are circumferentially arranged around the central axis of the engine; each guide vane has a rotation shaft, and the multiple guide vanes can synchronously rotate around the rotation shaft of each guide vane to close or open the first flow channel.

[0022] Further, the guide vane unit further comprises a rocker arm and a linkage ring; the linkage ring is arranged on the inner side of the guide vane inner ring; the rotation shaft is arranged on one end of the rocker arm, and the other end of the rocker arm is arranged on the linkage ring.

[0023] Further, the outer wall of the bleed ring is circumferentially provided with a roller groove; and the length direction of the roller groove is the same as the width direction of the bleed ring.

[0024] The part wall of the turbine inter-stage support outer wall extends outwardly with an extension; the extension comprises a first section and a second section; the first section connects the part wall of the turbine inter-stage support outer wall and the second section;

[0025] The first section is obliquely provided with a roller support, an end of the roller support is provided with a roller, and the roller is arranged in a roller groove and can roll in the roller groove.

[0026] Further, a driving unit is further included; the driving unit is used for driving the rotation of the guide vane and the opening and closing movement of the bleed ring; the driving unit can make the guide vane rotate to close the first flow channel while making the first end face and the second end face have a gap to open the second flow channel; and make the first end face and the second end face abut while making the guide vane rotate to open the first flow channel.

[0027] Further, the driving unit comprises a driving piece and a crank structure;

[0028] One end of the crank structure is connected with the output end of the driving piece, and the other end of the crank structure is arranged on the bleed ring;

[0029] The rotating shaft of one of the guide vanes has an extension end, and the extension end is arranged through the inner casing and connected with the crank structure.

[0030] Further, the crank structure comprises a first crank, a second crank and a third crank; the second crank is arranged between the first crank and the third crank; the first crank and the second crank both have a connecting part and a through part;

[0031] The connecting part of the first crank is connected with the output end of the driving piece, the through part of the first crank is arranged through the turbine outer casing and coaxially connected with the through part of the second crank; the connecting part of the second crank is connected with one end of the third crank, and the other end of the third crank is arranged on the bleed ring;

[0032] The through part of the second crank is connected with the extension end of the rotating shaft.

[0033] The second aspect of the present application provides a turbine, comprising a turbine rotor and the turbine rotor overspeed protection device; the turbine rotor is arranged on the side of the guide vane away from the first flow channel; the rotor is provided with a rotor speed sensor.

[0034] The third aspect of the present application provides an aero-engine comprising the turbine.

[0035] Compared with the prior art, the present application can at least achieve one of the following beneficial effects:

[0036] (1) Compared to existing over-speed protection devices that damage the rotor and thus cause engine losses, this invention provides a second flow channel for guiding the high-temperature combustion gas. After the rotor reaches a predetermined speed, the main flow channel of the combustion gas that performs work on the rotor, namely the first flow channel, is closed, allowing the combustion gas to flow out through the second flow channel. The combustion gas stops performing work on the turbine rotor, thereby limiting the rotor speed from further increasing and protecting the rotor. This invention does not damage the rotor and avoids damage to more parts from flying blades and other rotor fragments, ensuring that the entire engine operates normally after over-speed protection, stabilizing the engine system and improving operational safety.

[0037] (2) In this invention, the outer ring of the guide vane is connected to the wall of the first flow channel. When the gas flows out, it flows out through the first vent hole of the outer ring of the guide vane. The first vent hole forms a first guide for the gas. When the vent ring is open, there is a gap between the first end face and the second end face. The gap forms a second guide for the gas. The gas flowing out of the first vent hole enters the second cavity. The inner casing wall of the turbine is provided with a second vent hole. The gas in the second cavity enters the third cavity through the second vent hole. The second vent hole forms a third guide for the gas. The third cavity is connected to the outside, so that the gas can pass to the outside. The first vent hole, the gap, the second cavity, the second vent hole, and the third cavity form a second flow channel for guiding the gas flow.

[0038] (3) The roller bracket is inclinedly set on the extension, and the extension provides support for it; the roller rolls in the roller groove, providing guidance for the movement of the venting ring.

[0039] (4) The present invention provides a rocker arm and a linkage ring in the inner ring of the guide vane so that multiple guide vanes can rotate synchronously. When the guide vane rotates to the point where there is no gap between adjacent guide vanes, the first flow channel of gas to the rotor is closed and the gas cannot reach the rotor. When the guide vane rotates to the point where there is a gap between adjacent guide vanes, the first flow channel of gas to the rotor is opened.

[0040] (5) In this invention, the drive unit includes a drive component and a crank structure. The drive component drives the crank structure, so that the rotation of the crank structure drives the movement of the venting ring, so that the first end face of the venting ring abuts against or has a gap with the second end face of the platform portion of the outer ring of the guide vane, and drives the rotation of the guide vane through the connection with one of the guide vanes, opening or closing the first flow channel. The structure is simple and easy to operate, and the rotation of the guide vane is synchronized with the opening and closing of the second flow channel through the movement of the actuator, making the operation highly efficient.

[0041] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the specification or be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained from the content specifically pointed out in the text and accompanying drawings. Attached Figure Description

[0042] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0043] Figure 1 This is one of the structural schematic diagrams of the turbine rotor overspeed protection device in Example 1;

[0044] Figure 2 This is a schematic diagram of the structure of the first and second flow channels in Example 1;

[0045] Figure 3 This is the second schematic diagram of the turbine rotor overspeed protection device in Example 1;

[0046] Figure 4 This is a schematic diagram of the linkage ring and rocker arm in Example 1;

[0047] Figure 5 This is a schematic diagram of the structure of the vent ring, roller bracket, and roller in Example 1;

[0048] Figure 6 This is the third schematic diagram of the turbine rotor overspeed protection device in Example 1;

[0049] Figure 7 This is a schematic diagram of the crank structure in Example 1.

[0050] Figure label:

[0051] 1-Guide vane unit; 11-Guide vane; 111-Rotating shaft; 12-Guide vane inner ring; 13-Guide vane outer ring; 131-First vent hole; 132-Platform section; 1321-Second end face; 14-Rocker arm; 15-Linkage ring; 2-First cavity; 21-Interstage support inner wall; 22-Interstage support outer wall; 221-Step structure; 2211-Erection section; 222-Extension section; 2221-Roller bracket; 2222-Roller; 3-Vent ring; 31-Erection end; 32-First end face; 33-Roller groove; 4-Inner casing; 41-Second vent hole; 5-Outer casing; 6-Drive unit; 61-Actuator cylinder; 62-First crank; 63-Second crank; 64-Third crank. Detailed Implementation

[0052] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0053] Example 1

[0054] One specific embodiment of the present application, as shown in Figure 1 and Figure 2 A turbine rotor overspeed protection device is disclosed, which comprises a guide vane unit 1 and a first flow channel and a second flow channel for guiding high-temperature gas.

[0055] The guide vane unit 1 comprises guide vanes 11 for rectifying the gas driving the rotation of the turbine rotor; the first flow channel is communicated with the guide vanes 11.

[0056] When the turbine rotor reaches a predetermined rotational speed, the guide vanes 11 close the first flow channel and open the second flow channel.

[0057] When the second flow channel is opened, one end of the second flow channel is communicated with the first flow channel, and the other end of the second flow channel is communicated with the outside.

[0058] Compared with the prior art, the overspeed protection device causes damage to the rotor, thereby causing loss to the engine. The present embodiment sets the second flow channel for guiding high-temperature gas, and after the rotor reaches the predetermined rotational speed, the main gas flow channel, i.e. the first flow channel, for working on the rotor is closed, so that the gas flows out of the outside through the second flow channel, and the gas stops working on the turbine rotor, thereby limiting the further increase of the rotational speed of the rotor to protect the rotor. The present application does not damage the rotor, ensures the normal operation of the entire engine after the overspeed protection, makes the engine system stable, and improves the operation safety.

[0059] Specifically, as shown in Figure 3 The guide vane unit 1 comprises guide vanes 11, a guide vane inner ring 12 coaxially arranged with the engine, and a guide vane outer ring 13. The guide vanes 11 are arranged in plurality, and the plurality of guide vanes 11 are circumferentially arranged between the guide vane inner ring 12 and the guide vane outer ring 13 around the central axis of the engine.

[0060] Each guide vane 11 has a rotation shaft 111, and both ends of the rotation shaft 111 are arranged on the guide vane outer ring 13 and the guide vane inner ring 12, respectively. The guide vane 11 can rotate around the rotation shaft 111 thereof.

[0061] As shown in Figure 4 The guide vane unit 1 further comprises a rocker arm 14 and a linkage ring 15.

[0062] The linkage ring 15 is arranged on the inner side of the guide vane inner ring 12, and the linkage ring 15 is coaxial with the guide vane inner ring 12.

[0063] The rocker arm 14 is used to connect the rotating shaft 111 of the guide vane 11 and the linkage ring 15. The rotating shaft 111 is arranged at one end of the rocker arm 14, and the other end of the rocker arm 14 is arranged on the linkage ring 15 and can rotate relative to the linkage ring 15. When one of the guide vanes 11 rotates, the rotating shaft 111 drives the rocker arm 14 to rotate and swing, and the rocker arm 14 transmits the rotating motion to the linkage ring 15, which drives the other rocker arms 14 to rotate, and the other rocker arms 14 drive the rotating shafts 111 of the other guide vanes 11 to rotate, so that all the guide vanes 11 rotate synchronously.

[0064] The plurality of guide vanes 11 rotate synchronously around their rotating shafts 111. During rotation, when there is no gap between adjacent guide vanes 11, the first flow channel is closed; when there is a gap between adjacent guide vanes 11, the first flow channel is opened.

[0065] In this embodiment, the rocker arm 14 and the linkage ring 15 are arranged in the inner ring 12 of the guide vane, so that the plurality of guide vanes 11 can rotate synchronously. When the guide vanes 11 rotate to the state that there is no gap between adjacent guide vanes 11, the first flow channel for the gas to the rotor is closed, and the gas cannot reach the rotor; when the guide vanes 11 rotate to the state that there is a gap between adjacent guide vanes 11, the first flow channel for the gas to the rotor is opened. After the first flow channel is closed, the gas cannot reach the rotor and cannot do work on the rotor, and the rotating speed of the rotor decreases.

[0066] Further, as shown in Figure 4 , the wall surface of the outer ring 13 of the guide vane is circumferentially provided with a plurality of first gas discharge holes 131 for allowing the gas in the first flow channel to enter the outside of the outer ring 13 of the guide vane through the first gas discharge holes 131.

[0067] As shown in Figure 2 , the turbine inter-stage support outer wall 21 and the turbine inter-stage support inner wall 22 form a first cavity 2, and the first flow channel is formed in the first cavity 2. As shown in Figure 5 , the edge of the turbine inter-stage support outer wall 21 has a stepped structure 221, and the edge of the outer ring 13 of the guide vane abuts against the stepped structure 221. It should be noted that, in order to seal the first cavity 2, a sealing ring is arranged between the outer ring 13 of the guide vane and the stepped structure 221.

[0068] Further, the gas discharge unit is also included. As shown in Figure 5 , the gas discharge unit includes a gas discharge ring 3 arranged outside the outer ring 13 of the guide vane. The gas discharge ring 3 has a gap with the outer ring 13 of the guide vane.

[0069] The turbine stage interstage support outer wall 21 has an outwardly stepped structure 221 at its edge; the venting ring 3 rests on the outside of the stepped structure 221. The venting ring 3 has an attachment end 31, the upper part of the stepped structure 221 is the attachment portion 2211, and the inner wall of the attachment end 31 rests on the attachment portion 2211. The attachment portion 2211 is provided with a groove for placing a sealing ring, so that the venting ring 3 and the attachment portion 2211 are sealed together. The venting ring 3 is movable relative to the attachment portion 2211.

[0070] The end face of the venting ring 3 furthest from the erection end 31 is the first end face 32; a portion of the outer wall of the guide vane outer ring 13 extends to one side to form a platform portion 132, the end face of which is the second end face 1321. When the venting ring 3 moves relative to the erection portion 2211, the first end face 32 and the second end face 1321 come into contact or have a gap.

[0071] When the venting ring 3 moves away from the erection part 2211, the first end face 32 abuts against the second end face 1321, and there is no gap between the venting ring 3 and the platform part 132. A cavity is formed between the venting ring 3, the erection part 2211, and the outer ring 13 of the guide vane. The gas in the first flow channel enters the cavity through the first venting hole 131. When the venting ring 3 moves towards the erection part 2211, there is a gap between the first end face 32 and the second end face 1321. The gas in the first flow channel passes through the first venting hole 131 to neutralize the gap between the first end face 32 and the second end face 1321 and flows to the outside of the venting ring 3.

[0072] A portion of the outer wall of the turbine stage support 22 extends outward to form an extension 222. The extension 222 includes a first section and a second section. The first section is obliquely arranged, and the second section is horizontally arranged. The end of the second section is connected to the inner casing 4 of the turbine. The turbine stage support outer wall 22, the guide vane outer ring 13, the bleed ring 3, and the inner casing 4 form a second cavity. When the bleed ring 3 is open and there is a gap between the first end face 32 and the second end face 1321, the combustion gas flows from the gap into the second cavity.

[0073] It should be noted that the inner casing 4 of the turbine is provided with a second vent hole 41 in the circumferential direction, and the gas in the second cavity is discharged to the outside of the inner casing 4 through the second vent hole 41.

[0074] An outer casing 5 with a turbine is disposed outside the inner casing 4, forming a third cavity between the inner casing 4 and the outer casing 5. The third cavity opens to the outside. The combustion gas in the second cavity passes through the second vent 41 to the third cavity and is discharged to the outside.

[0075] like Figure 2 As shown, when there is a gap between the first end face 32 of the venting ring 3 and the second end face 1321 of the platform portion 132 of the guide vane outer ring 13, the first venting hole 131, the gap, the second cavity, the second venting hole 41, and the third cavity form a second flow channel.

[0076] The outer wall of the venting ring 3 is provided with a roller groove 33 in the circumferential direction. The length direction of the roller groove 33 is the same as the width direction of the venting ring 3. A roller bracket 2221 extends obliquely from the inner wall of the extension 222. A roller 2222 is provided at the end of the roller bracket 2221. The roller 2222 is disposed in the roller groove 33 and can roll in the roller groove 33.

[0077] The roller bracket 2221 is inclinedly disposed on the extension 222, and the extension 222 provides support for it; the roller 2222 rolls in the roller groove 33, providing guidance for the movement of the venting ring 3.

[0078] In this embodiment, the outer ring 13 of the guide vane is connected to the wall of the first flow channel. When the gas flows out, it flows out through the first vent hole 131 of the outer ring 13 of the guide vane, and the first vent hole 131 forms a first guide for the gas. When the vent ring 3 is open, there is a gap between the first end face 32 and the second end face 1321, and the gap forms a second guide for the gas. The gas flowing out of the first vent hole 131 enters the second cavity. The wall of the turbine inner casing 4 is provided with a second vent hole 41. The gas in the second cavity enters the third cavity through the second vent hole 41, and the second vent hole 41 forms a third guide for the gas. The third cavity is connected to the outside, allowing the gas to pass to the outside. Figure 2 As shown, the first vent 131, the gap, the second cavity, the second vent 41, and the third cavity form a second flow channel for guiding the flow of gas.

[0079] Furthermore, it also includes a drive unit 6. The drive unit 6 is used to drive the rotation of the guide vane 11 and the opening and closing motion of the venting ring 3. For example... Figure 6 and Figure 7 As shown, the drive unit 6 can rotate the guide vane 11 to close the first flow channel while creating a gap between the first end face 32 and the second end face 1321 to open the second flow channel; and can rotate the guide vane 11 to open the first flow channel while the first end face 32 and the second end face 1321 come into contact.

[0080] Exemplarily, the drive unit 6 includes a drive member and a crank structure. Exemplarily, the drive member is an actuating cylinder 61.

[0081] like Figure 7 As shown, one end of the crank structure is connected to the output end of the drive component, and the other end of the crank structure is mounted on the venting ring 3. The rotation of the crank structure drives the movement of the venting ring 3. One of the guide vanes 11 has an extension end on its shaft 111. The extension end passes through the inner casing 4 and is connected to the crank structure. The rotation of the crank structure drives the guide vane 11 to rotate.

[0082] The crank structure can be a whole crank, a combination of multiple cranks, or a combination of a crank and other components. In the embodiment, the crank structure includes a first crank 62, a second crank 63, and a third crank 64.

[0083] The second crank 63 is arranged between the first crank 62 and the third crank 64. Both the first crank 62 and the second crank 63 have a connecting portion and a passing portion. The passing portion of the second crank 63 is connected to the extended end of the rotating shaft 111.

[0084] The connecting portion of the first crank 62 is connected to the output end of the driving member, and the passing portion of the first crank 62 passes through the turbine outer casing 5 and is coaxially connected to the passing portion of the second crank 63. The connecting portion of the second crank 63 is connected to one end of the third crank 64, and the other end of the third crank 64 is arranged on the gas bleeding ring 3.

[0085] The actuating cylinder 61 performs extension and retraction movements.

[0086] When the actuating cylinder 61 extends, the connecting portion of the first crank 62 rotates clockwise, the passing portion of the first crank 62 rotates clockwise, the passing portion of the second crank 63 coaxial with the passing portion of the first crank 62 rotates clockwise, the rotating shaft 111 connected to the guide vane 11 rotates clockwise, there is no gap between adjacent guide vanes 11, the first flow passage is closed, the connecting portion of the second crank 63 swings clockwise, the third crank 64 swings clockwise, the end of the third crank 64 connected to the gas bleeding ring 3 moves away from the platform portion 132, a gap is formed between the first end face 32 and the second end face 1321, the gas bleeding ring 3 is opened, the gas passes through the first gas bleeding hole 131, the gap, the second cavity, the second gas bleeding hole 41, and the third cavity to the outside, and the rotating speed of the rotor is reduced.

[0087] When the actuating cylinder 61 retracts, the connecting portion of the first crank 62 rotates counterclockwise, the passing portion of the first crank 62 rotates counterclockwise, the passing portion of the second crank 63 coaxial with the passing portion of the first crank 62 rotates counterclockwise, the rotating shaft 111 connected to the guide vane 11 rotates counterclockwise, there is a gap between adjacent guide vanes 11, the first flow passage is opened, the connecting portion of the second crank 63 swings counterclockwise, the third crank 64 swings counterclockwise, the end of the third crank 64 connected to the gas bleeding ring 3 moves towards the platform portion 132, until the first end face 32 abuts against the second end face 1321, the gas bleeding ring 3 is closed, and the second flow passage is closed.

[0088] The driving unit 6 in the embodiment comprises a driving member and a crank structure, the driving member drives the crank structure, the rotation of the crank structure drives the movement of the air release ring 3, the first end surface 32 of the air release ring 3 abuts against or has a gap with the second end surface 1321 of the platform part 132 of the guide vane outer ring 13, and the rotation of the guide vane 11 is driven through the connection with one of the guide vanes 11, the first flow channel is opened or closed, the structure is simple and easy to operate, and the rotation of the guide vane 11 is synchronized with the opening and closing of the second flow channel through the movement of the actuating cylinder 61, the operation is efficient.

[0089] Embodiment 2

[0090] The embodiment discloses a turbine comprising a rotor and the turbine rotor overspeed protection device in embodiment 1. The rotor is arranged on the side of the guide vane 11 away from the first flow channel; the rotor is provided with a rotor speed sensor.

[0091] Further, a control mechanism is further included. When the rotor speed exceeds the predetermined speed, the speed sensor feeds back to the control mechanism, the control mechanism controls the movement of the driving member, drives the movement of the crank structure, and opens the second flow channel.

[0092] Compared with the prior art, the turbine in the embodiment has the same advantages as the turbine rotor overspeed protection device in embodiment 1, which will not be repeated here.

[0093] Embodiment 3

[0094] The embodiment discloses an aero-engine comprising the turbine in embodiment 2.

[0095] Compared with the prior art, the aero-engine in the embodiment has the same advantages as the turbine in embodiment 2, which will not be repeated here.

[0096] The above is only a preferred specific embodiment of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A turbine rotor overspeed protection device, characterized in that, It includes a guide vane unit (1) and a first flow channel and a second flow channel for guiding high-temperature gas flow; The guide vane unit (1) includes a guide vane (11), which is used to rectify the gas flow that drives the turbine rotor to rotate; the first flow channel is connected to the guide vane (11); When the turbine rotor reaches the predetermined speed, the guide vane (11) closes the first flow channel and opens the second flow channel; When the second flow channel is opened, one end of the second flow channel is connected to the first flow channel, and the other end of the second flow channel is connected to the outside, so as to reduce the high-heat gas passing through the turbine rotor.

2. The turbine rotor overspeed protection device according to claim 1, characterized in that, The guide vane unit (1) also includes a guide vane outer ring (13) coaxially arranged with the engine; the guide vane outer ring (13) has a first vent hole (131) circumferentially arranged on the side wall.

3. The turbine rotor overspeed protection device according to claim 2, characterized in that, It also includes a venting unit; the venting unit includes a venting ring (3); the venting ring (3) is disposed outside the outer ring (13) of the guide vane, and the venting ring (3) can cover the first venting hole (131).

4. The turbine rotor overspeed protection device according to claim 3, characterized in that, The outer wall of the guide vane outer ring (13) extends to one side to form a platform portion (132); the venting ring (3) is able to move to one side of the platform portion (132) and abut against or have a gap with the platform portion (132).

5. The turbine rotor overspeed protection device according to claim 4, characterized in that, The end face of the venting ring (3) near the platform part (132) is the first end face (32), and the end face of the platform part (132) is the second end face (1321); when the venting ring (3) abuts against the platform part (132), the first end face (32) and the second end face (1321) are in contact.

6. The turbine rotor overspeed protection device according to claim 5, characterized in that, The inner casing (4) of the turbine is located outside the outer ring (13) of the guide vane, and the end of the inner casing (4) is connected to the outer wall (22) of the turbine stage support. The turbine stage interstage support outer wall (22), the guide vane outer ring (13), the venting ring (3), and the inner casing (4) form a second cavity; The inner casing (4) is provided with a second vent hole (41) circumferentially on the wall surface; The inner casing (4) is externally provided with an outer casing (5) containing a turbine; the outer casing (5) and the inner casing (4) form a third cavity; the third cavity is connected to the outside; The venting ring (3) moves away from the platform portion (132) to create a gap between the first end face (32) and the second end face (1321). The first venting hole (131), the gap, the second cavity, the second venting hole (41), and the third cavity form a second flow channel. The venting ring (3) moves toward the side closer to the platform (132), so that the first end face (32) fits against the second end face (1321), and the second flow channel is closed.

7. The turbine rotor overspeed protection device according to claim 2, characterized in that, The guide vane unit (1) also includes a guide vane inner ring (12) coaxially arranged with the engine; the two ends of the guide vane (11) are respectively arranged on the guide vane inner ring (12) and the guide vane outer ring (13); Multiple guide vanes (11) are provided, and the multiple guide vanes (11) are arranged circumferentially around the central axis of the engine; each guide vane (11) has a rotating shaft (111), and the multiple guide vanes (11) can rotate synchronously around their own rotating shaft (111) to close or open the first flow channel.

8. The turbine rotor overspeed protection device according to claim 7, characterized in that, The guide vane unit (1) further includes a rocker arm (14) and a linkage ring (15), the linkage ring (15) being disposed on the inner side of the inner ring (12) of the guide vane; the rotating shaft (111) is disposed on one end of the rocker arm (14), and the other end of the rocker arm (14) is disposed on the linkage ring (15).

9. The turbine rotor overspeed protection device according to claim 5, characterized in that, The outer wall of the venting ring (3) is provided with a roller groove (33) in the circumferential direction, and the length direction of the roller groove (33) is the same as the width direction of the venting ring (3); A portion of the outer wall of the turbine stage support (22) extends outward to form an extension (222); the extension (222) includes a first section and a second section; the first section connects a portion of the outer wall of the turbine stage support (22) and the second section; the first section is obliquely provided with a roller bracket (2221), and the end of the roller bracket (2221) is provided with a roller (2222), the roller (2222) is disposed in the roller groove (33) and can roll in the roller groove (33).

10. The turbine rotor overspeed protection device according to claim 6, characterized in that, It also includes a drive unit (6); the drive unit (6) is used to drive the guide vane (11) to rotate and the venting ring (3) to open and close; the drive unit (6) can make the guide vane (11) rotate to close the first flow channel while making the first end face (32) and the second end face (1321) have a gap to open the second flow channel; and make the first end face (32) abut against the second end face (1321) while making the guide vane (11) rotate to open the first flow channel.

11. The turbine rotor overspeed protection device according to claim 10, characterized in that, The drive unit (6) includes a drive component and a crank structure; One end of the crank structure is connected to the output end of the drive component, and the other end of the crank structure is disposed on the venting ring (3); One of the guide vanes (11) has an extension end on its shaft, which passes through the inner casing (4) and is connected to the crank structure.

12. The turbine rotor overspeed protection device according to claim 11, characterized in that, The crank structure includes a first crank (62), a second crank (63), and a third crank (64); the second crank (63) is disposed between the first crank (62) and the third crank (64); both the first crank (62) and the second crank (63) have a connecting part and a through part; The connecting part of the first crank (62) is connected to the output end of the drive unit, the through part of the first crank (62) passes through the outer casing (5) and is coaxially connected with the through part of the second crank (63); the connecting part of the second crank (63) is connected to one end of the third crank (64), and the other end of the third crank (64) is disposed on the vent ring (3); The through portion of the second crank (63) is connected to the extension end of the shaft.

13. A turbine, characterized in that, Includes a turbine rotor and a turbine rotor overspeed protection device as described in any one of claims 1-12, wherein the turbine rotor is disposed on the side of the guide vane (11) opposite to the first flow channel; the rotor is provided with a rotor speed sensor.

14. An aircraft engine, characterized in that, Including the turbine as described in claim 13.

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