CN110847982B - A combined high-pressure turbine rotor outer ring cooling and sealing structure - Google Patents

Abstract

The invention discloses a combined high-pressure turbine rotor outer ring cooling and sealing structure, comprising a combustion outdoor casing, a high-pressure turbine rotor outer ring and an auxiliary sealing structure. The opposite surfaces of the blades on the outer ring of the turbine rotor are coated with a high temperature resistant wearable coating, and by opening the impingement cooling holes in the outer casing of the combustion chamber along the circumferential direction, and by forming the outer casing between the outer casing of the combustion chamber and the outer ring of the high pressure turbine rotor The improvement of the connecting structure makes a cold air cavity formed between the two, thereby realizing the efficient cooling of the outer ring of the high-pressure turbine rotor through the impact of cold air jets, and at the same time, the auxiliary sealing structures such as sealing rings and sealing baffles are provided to seal the rotor. Strictly cool the air, thereby reducing the thermal load of the high-temperature component, the outer ring of the high-pressure turbine rotor, making the thermal deformation of the hot-end component controllable, reducing the amount of cold air, maximizing the cooling effect, and improving the stability and reliability of the structure.

Description

A combined high-pressure turbine rotor outer ring cooling and sealing structure

technical field

The invention relates to the fields of aero-engines and gas turbines, in particular to the improvement of the cooling and sealing structure of the outer ring of a high-pressure turbine rotor. , The method of high temperature wearable coating improves the cooling and sealing effect, reduces the thermal load of this high temperature component, and improves the stability and reliability of the structure.

Background technique

The outer ring of the high-pressure turbine rotor is located downstream of the high-pressure turbine guide, close to the outlet of the combustion chamber, and directly contacts the high-temperature gas at the outlet of the combustion chamber. It is one of the components with the highest temperature and the worst working conditions in the engine. For the outer ring of the high-pressure turbine rotor and its adjacent combustion outdoor casing, on the one hand, the ambient temperature is usually above 800°C, and the inside is the mainstream high-temperature gas, the outside is the cold air from the high-pressure compressor outlet, and the temperature difference between the inside and outside is large, high absolute temperature. On the other hand, the size of the casing outside the combustion chamber is large, and the thermal deformation is difficult to control.

The combustion outdoor casing is usually processed in one piece, which is difficult and expensive to process, and as a frame structure, it is necessary to ensure that its structure is reliable. Therefore, it is necessary to isolate and protect the casing outside the combustion chamber to prevent it from coming into direct contact with high-temperature gas. This function is usually performed by the outer ring of the high pressure turbine rotor located between the rotor blades and the outer casing of the combustion chamber. The outer ring of the high-pressure turbine rotor is directly in contact with the high-temperature gas, and the temperature is high and the thermal stress is large, which requires efficient cooling. Its cooling design needs to be fine enough to ensure that its thermal deformation is controllable, to ensure that the rotor and the stator coordinate deformation, and to make the gap between the rotor blade tip and the casing as small as possible to reduce the mainstream aerodynamic loss. At the same time, the air volume used for cooling should be kept as small as possible in order to improve the efficiency of the whole machine.

Existing high pressure turbine rotor outer ring designs generally fall into two categories. One design is an integral structure of the whole ring, which may cause deformation due to excessive local extrusion stress under the condition of uneven heating. This deformation may be more obvious under the action of the huge pressure difference inside and outside the outer ring of the high-pressure turbine rotor. Once the outer ring of the high-pressure turbine rotor of the whole ring type is damaged, it needs to be replaced as a whole, resulting in high cost and poor maintainability. Another design is a split-lobe structure, but there is a large gap between the outer rings of the high-pressure turbine rotor for each two lobes, which is not sealed, resulting in a large consumption of gas for cooling and sealing. Therefore, it is urgent to propose a new type of cooling and sealing structure according to the working environment and structural characteristics of the outer ring of the high-pressure turbine rotor and its adjacent combustion casing and the rotor blades of the high-pressure turbine, so as to achieve high maintainability and reduce maintenance. At the same time, the thermal deformation of the hot end component is controllable, and the amount of cold air is reduced.

SUMMARY OF THE INVENTION

In view of the above technical requirements, the present invention proposes a combined high-pressure turbine rotor outer ring cooling and sealing structure. Coated with high temperature wearable coating, and by opening impact cooling holes in the outer casing of the combustion chamber along the circumferential direction, the high-efficiency cooling of the outer ring of the high-pressure turbine rotor can be achieved through the impact of cold air jets. The auxiliary sealing structure is used to seal the cold air, so as to reduce the thermal load of the high-temperature component, the outer ring of the high-pressure turbine rotor, make the thermal deformation of the hot-end component controllable, reduce the amount of cold air, maximize the cooling effect, and improve the structure. stability and reliability.

For realizing above-mentioned technical goal, the technical scheme adopted in the present invention is as follows:

A combined high-pressure turbine rotor outer ring cooling sealing structure includes a combustion outdoor casing, a high-pressure turbine rotor outer ring and an auxiliary sealing structure. The high-pressure turbine rotor outer ring is assembled and arranged on the inner wall of the combustion outdoor casing, so the The auxiliary sealing structure is assembled between the outer casing of the combustion chamber and the outer ring of the high-pressure turbine rotor. The radially inner space of the outer ring of the high-pressure turbine rotor is a high-temperature gas channel, and a peripheral edge of the high-temperature gas channel is arranged in the high-temperature gas channel. The uniformly distributed high-pressure turbine rotor blades are characterized in that, the outer casing of the combustion chamber includes a casing of a one-piece integral ring structure, and the inner wall of the casing is provided with at least two axially spaced and The annular L-shaped corner structures arranged in parallel, the corner directions of the annular L-shaped corner structures are the same, and each of the annular L-shaped corner structures includes a first radial extension section and a first axial direction an extension section, the first axial extension section is located at the end of the first radial extension section; axially located on the casing between two adjacent annular L-shaped corner structures, Also provided with at least one row of impingement cooling holes distributed along the circumferential direction, the impingement cooling holes are used for introducing impingement cooling gas;

The outer ring of the high-pressure turbine rotor has a split structure as a whole, including a plurality of arc-shaped rotor outer ring segments, and at least two arc-shaped inverted rings with axial spacing and parallel arranged on the outer wall of each of the rotor outer ring segments are provided. L-shaped corner structures, the corner directions of each of the arc-shaped inverted L-shaped corner structures are the same, and each of the arc-shaped inverted L-shaped corner structures includes a second radial extension section and a second axial extension section, the second axially extending segment is disposed on the sidewall of the second radially extending segment, and there is a radial distance between the second axially extending segment and the end of the second radially extending segment; Each of the rotor outer ring segments is assembled and arranged on each of the annular L-shaped corner structures of the combustion outdoor casing through the arc-shaped inverted L-shaped corner structures provided on the outer wall thereof in a one-to-one correspondence; In the assembled state, the inner wall of the second axially extending section is fitted on the outer wall of the first axially extending section, and the end of the second radially extending section abuts against the casing shell On the inner wall of the rotor, and the axial space between the two pairs of mutually matched corner structures is formed as a cold air cavity; in the assembled state, there is also a circumferential gap between the two adjacent rotor outer ring segments, and even in the heat The circumferential gap is still maintained in the working state;

The auxiliary sealing structure includes an auxiliary sealing ring, a radial sealing baffle and a circumferential sealing baffle, wherein the outer wall of each second axially extending section and the inner wall of the casing shell A said auxiliary sealing ring is arranged in the radial clearance space between them; the circumferential two ends of each said rotor outer ring segment are respectively provided with a circumferential sealing baffle card slot, and two adjacent rotor outer ring segments A said circumferential sealing blocking piece is arranged between two adjacent circumferential sealing blocking piece slots, and both ends of the circumferential sealing blocking piece are respectively movably inserted in the two circumferential sealing blocking pieces. Each of the circumferential sealing baffles can seal the circumferential gap between the walls of two adjacent rotor outer ring segments in a one-to-one correspondence, even in a hot working state; The circumferential ends of each of the second radially extending segments on the outer wall of each of the rotor outer ring segments are respectively provided with a radial sealing baffle card slot, and the adjacent two adjacent rotor outer ring segments are adjacent to each other. A radial sealing baffle is arranged between the two radial sealing baffles, and the two ends of the radial sealing baffle are respectively movably inserted in the two radial sealing baffles. In the slot, and even in a hot working state, each of the radial sealing baffles can still seal the circumferential direction between the second radially extending segments of two adjacent rotor outer ring segments in a one-to-one correspondence. Clearance; the metal sealing ring works together with each of the circumferential sealing baffles and radial sealing baffles, so that even in a hot working state, the impact cooling gas in the cold air cavity will not leak .

In the above-mentioned combined high-pressure turbine rotor outer ring cooling and sealing structure of the present invention, the circumferentially distributed high-pressure turbine rotor blades are the opposite parts of the high-pressure turbine rotor outer ring. The outer ring of the traditional high-pressure turbine rotor is a whole ring. In the working state, the local stress is usually too large due to uneven heating. In the invention, the outer ring of the high-pressure turbine rotor is of a split-lobe structure, and there is a circumferential gap between the outer ring segments of the adjacent two-lobed rotors. When it is the highest), there is still a certain circumferential gap between the two adjacent rotor outer ring segments, and it will not die.

Preferably, in the outer ring of the high-pressure turbine rotor, each of the outer ring segments of the rotor is marked clockwise or counterclockwise with the angular zero point as the starting point, and is assembled according to the sequence number during installation to ensure that it is compatible with the combustion The relative position of the outdoor casing is fixed.

Preferably, an arc-shaped convex rib is provided on the outer side wall of the second radially extending section close to the upstream of each of the rotor outer ring segments, and in a hot working state, the arc-shaped convex rib is used to limit the The amount of movement along the axial direction of the outer ring of the high-pressure turbine rotor when it is heated and expanded and deformed.

Preferably, the number of split lobes is determined according to the temperature field distribution and strength checking results of the outer ring of the high-pressure turbine rotor under working conditions.

Preferably, a coating layer is provided on the inner wall of each of the rotor outer ring segments, and the coating layer is selected from high temperature and wearable materials. The coating material needs to be resistant to high temperature to prevent damage in high temperature environment.

Further, the hardness of the coating is lower than the hardness of the high-pressure turbine rotor blade, so as to ensure that the high-pressure turbine rotor blade will not be damaged when the two are scraped in a working state.

Preferably, the auxiliary sealing ring is made of silver-plated metal material to prevent sintering in a high temperature environment.

Preferably, the axial width of each of the circumferential sealing baffle grooves is greater than the axial distance between the two second radially extending segments on the outer wall of each of the rotor outer ring segments.

Preferably, each of the radial sealing baffle grooves should extend at least from the radial top end of the second radial extension segment to the radial bottom end thereof.

Preferably, the radial sealing baffles and the circumferential sealing baffles between the rotor outer ring segments are made of high-temperature alloys to prevent damage in a high temperature environment.

Preferably, by adjusting the cross-sectional area of the impact cooling hole, the amount of cold air impinging on the outer ring of the high-pressure turbine rotor can be precisely controlled, thereby accurately controlling the thermal deformation of the outer ring of the high-pressure turbine rotor, so as to ensure the high-pressure turbine rotor. The coordinated deformation between the outer ring and the casing outside the combustion chamber minimizes the radial distance between the tip of the high-pressure turbine rotor blade and the outer ring of the high-pressure turbine rotor, ensuring optimal aerodynamic performance. Different hole types and hole inclination angles can be selected comprehensively to further improve the impact cooling effect.

Preferably, the impingement cooling gas introduced into the impingement cooling holes is led out from the outlet of the high pressure compressor.

Preferably, the impingement cooling holes are evenly distributed on the casing shell along the circumferential direction.

Compared with the existing high-pressure turbine rotor outer ring cooling and sealing structure, the combined high-pressure turbine rotor outer ring cooling and sealing structure proposed in the present invention has the following advantages: 1. The high-pressure turbine rotor outer ring adopts a split structure to prevent Extrusion deformation caused by thermal stress concentration. 2. The split high-pressure turbine rotor outer ring is radially located between the outer casing of the combustion chamber and the main flow passage of the high temperature gas, which prevents the direct contact between the high temperature gas and the outer casing of the combustion chamber and protects the outer casing of the combustion chamber. 3. Each lobe of the outer ring of the high-pressure turbine rotor is provided with a fixed number, and the relative position to the outer casing of the combustion chamber is fixed. The installation and disassembly process are carried out in sequence, and the disassembly and assembly are simple and reliable. 4. On the outer casing of the combustion chamber, there are impact cooling holes along the circumferential direction to perform impact cooling on the outer ring of the high-pressure turbine rotor. The impact cooling efficiency is high and the cooling effect is good. Under the same cooling effect, it can reduce the consumption of cold air and improve the efficiency of the whole machine. . 5. The impact cooling gas is led out from the outlet of the high-pressure compressor, the air bleed path is short, and the loss along the way is small. The gas velocity at the entrance of the impinging cooling hole is close to the speed of sound, and its flow rate can be determined by the cross-sectional area of the cooling hole. By adjusting the cross-sectional area of the hole, the amount of cold air impacting the outer ring of the rotor can be precisely controlled, and then the thermal deformation of the outer ring of the rotor can be precisely controlled to ensure that the outer ring of the high-pressure turbine rotor does not overheat and rotates, and the stator deforms in harmony. 6. In order to make the impact cooling more effective, in the radial and circumferential directions, a baffle slot and a sealing baffle are arranged between the outer ring segments of each two-lobed rotor to block and seal the cooling and sealing gas. The diversion prevents the cooling gas from leaking through the gap between the two lobes, so that the axial and circumferential coverage of the cooling gas is higher, and the cooling effect is better. 7. A high-temperature-resistant metal sealing ring is used between the outer casing of the combustion chamber and the outer ring of the high-pressure turbine rotor, which prevents the mainstream high-temperature gas from contacting the outer casing of the combustion chamber through the gap between the two. The cooling gas inside the cooling cavity formed by the casing is effectively sealed to ensure that all the cold air is located in the cavity for cooling. 8. The inner wall of the outer ring of the high-pressure turbine rotor is coated with a high-temperature abradable coating to prevent the blades from being damaged when the high-pressure turbine rotor blades and the outer ring of the high-pressure turbine rotor are scraped due to too small clearance.

Description of drawings

1 is a schematic diagram of the cooling and sealing structure of the combined high-pressure turbine rotor outer ring of the present invention;

2 is a schematic diagram of the overall structure of the combustion outdoor casing of the present invention;

3 is a sectional view of the combustion outdoor casing of the present invention;

Fig. 4 is a partial enlarged view of the cross-section of the external casing of the combustion chamber of the present invention;

5 is a schematic diagram of the overall structure of the rotor outer ring segment of the present invention;

Figure 6 is a sectional view of the rotor outer ring segment of the present invention;

Fig. 7 is the assembly schematic diagram of the auxiliary sealing ring in the auxiliary sealing structure of the present invention;

FIG. 8 is a schematic view of the assembly of radial and circumferential sealing baffles in the auxiliary sealing structure of the present invention.

Detailed ways

In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail below with reference to the accompanying drawings and embodiments.

As shown in FIG. 1, the combined high-pressure turbine rotor outer ring cooling sealing structure of the present invention includes a combustion outdoor casing 1, a high-pressure turbine rotor outer ring 2 and an auxiliary sealing structure 3, wherein the high-pressure turbine rotor outer ring 2 is assembled It is arranged on the inner wall of the combustion outdoor casing 1. An auxiliary sealing structure 3 is assembled between the combustion outdoor casing 1 and the high-pressure turbine rotor outer ring 2. The radial inner space of the high-pressure turbine rotor outer ring 2 is a high-temperature gas channel. The high-temperature gas passage is provided with high-pressure turbine rotor blades 4 evenly distributed along the circumferential direction, and the circumferentially distributed high-pressure turbine rotor blades 4 are the opposite parts of the outer ring 2 of the high-pressure turbine rotor.

As shown in FIGS. 2 to 4 , in the combined high-pressure turbine rotor outer ring cooling and sealing structure of the present invention, the combustion outdoor casing 1 includes a casing casing 101 in an integral ring structure, and the inner wall of the casing casing 101 There are at least two annular L-shaped corner structures 102 with axial spacing and arranged in parallel. A longitudinal extension section and a first axial extension section, the first axial extension section is located at the end of the first radial extension section; the casing is located between two adjacent annular L-shaped corner structures 102 in the axial direction 101 is also provided with at least one row of impingement cooling holes 104 evenly distributed in the circumferential direction. The impingement cooling holes 104 are used to introduce impingement cooling gas, and the impingement cooling gas introduced into the impingement cooling holes 104 is led out from the outlet of the high pressure compressor.

In the example of the present invention, by adjusting the cross-sectional area of the impact cooling hole 104, the amount of cold air impinging on the outer ring of the high-pressure turbine rotor can be precisely controlled, and the thermal deformation of the outer ring 2 of the high-pressure turbine rotor can be precisely controlled to ensure that the outer ring of the high-pressure turbine rotor is accurately controlled. The coordinated deformation between 2 and the combustion outdoor casing 1 minimizes the radial distance between the tip of the high-pressure turbine rotor blade 4 and the outer ring 2 of the high-pressure turbine rotor to ensure optimal aerodynamic performance. In addition, different hole types and hole inclination angles can be comprehensively selected to further improve the impact cooling effect.

The outer ring of the traditional high-pressure turbine rotor is a whole ring. Under the working state, the local stress is usually too large due to uneven heating. In the combined high-pressure turbine rotor outer ring cooling and sealing structure of the present invention, the high-pressure turbine rotor outer ring is a split-lobe structure, and a circumferential gap is left between the adjacent two-lobe rotor outer ring segments. To ensure that in the hot working state (ie, when the temperature is the highest), there is still a certain circumferential gap between the outer ring segments of the adjacent two-lobed rotors, and it will not die. Specifically, as shown in FIGS. 5 and 6 , in the present invention, the high-pressure turbine rotor outer ring 2 has a split-lobed structure as a whole, and includes a plurality of lobed arc-shaped rotor outer ring segments, and the outer wall of each rotor outer ring segment is provided with at least Two arc-shaped inverted L-shaped corner structures 203 are arranged in parallel with an axial spacing, the corners of the arc-shaped inverted L-shaped corner structures 203 are in the same direction, and each arc-shaped inverted L-shaped corner structure 203 includes a second radial The extension section and a second axial extension section, the second axial extension section is arranged on the side wall of the second radial extension section, and there is a space between the second axial extension section and the end 201 of the second radial extension section Radial distance; each rotor outer ring segment is assembled and arranged on each annular L-shaped corner structure 102 of the combustion outdoor casing 1 through each arc-shaped inverted L-shaped corner structure 203 arranged on its outer wall in a one-to-one correspondence; at In the assembled state, the inner wall 205 of the second axially extending section is fitted on the outer wall 103 of the first axially extending section, and the end 201 of the second radially extending section abuts against the inner wall of the casing 101, and The axial space between the two pairs of mutually matched corner structures is formed as a cold air cavity; in the assembled state, there is also a circumferential gap between the two adjacent rotor outer ring segments, and the circumferential gap is maintained even in the hot working state. to the gap.

In the example of the present invention, in the rotor outer ring 2 of the high-pressure turbine, each rotor outer ring segment is marked with a serial number clockwise or counterclockwise from the angular zero point, and is assembled according to the serial number during installation to ensure that it is compatible with the combustion outdoor casing. The relative position is fixed, the installation and disassembly process are carried out in sequence, the disassembly and assembly are simple, and the reliability is high.

In the example of the present invention, an arc-shaped convex rib 204 is provided on the outer side wall of the second radially extending section near the upstream of each rotor outer ring segment. In the hot working state, the arc-shaped convex rib 204 is used to Limit the amount of movement of the outer ring 2 of the high-pressure turbine rotor in the axial direction when it is expanded and deformed by heat.

In the example of the present invention, the number of split lobes is determined according to the temperature field distribution and strength checking results of the outer ring of the high-pressure turbine rotor in the working state.

In the example of the present invention, a coating layer 206 is provided on the inner wall of each rotor outer ring segment, and the coating layer is selected from a high-temperature wearable material. The coating material needs to be resistant to high temperature to prevent damage in high temperature environment. The hardness of the coating 206 is lower than the hardness of the high-pressure turbine rotor blade 4, so as to ensure that the high-pressure turbine rotor blade 4 will not be damaged when the two are scraped and worn in the working state.

As shown in Figures 7 and 8, in the combined high-pressure turbine rotor outer ring cooling sealing structure of the present invention, the auxiliary sealing structure 3 includes an auxiliary sealing ring 301, a radial sealing baffle 302 and a circumferential sealing baffle 303, wherein, an auxiliary sealing ring 301 is provided in the radial clearance space between the outer wall of each second axially extending segment and the inner wall of the casing 101; the circumferential ends of each rotor outer ring segment are respectively A circumferential sealing blocking piece 208 is provided, and a circumferential sealing blocking piece 303 is provided between the adjacent two circumferential sealing blocking piece grooves 208 of two adjacent rotor outer ring segments, and a circumferential sealing blocking piece 303 The two ends of the two circumferential sealing baffles 303 are respectively movably inserted into the two-way sealing baffle slot 208, and even in a hot working state, each circumferential sealing baffle 303 can still seal two adjacent rotor outer ring segments in a one-to-one correspondence. Circumferential gaps between the walls of each rotor outer ring segment; a radial sealing baffle card slot 207 is respectively set at the circumferential ends of each second radially extending segment on the outer wall of each rotor outer ring segment, and two adjacent rotor outer rings A radial sealing blocking piece 302 is arranged between the two adjacent radial sealing blocking piece slots 207 of the segment, and the two ends of the radial sealing blocking piece 302 are respectively movably inserted in the two radial sealing blocking piece cards. In the groove 207, and even in a hot working state, each radial sealing baffle 302 can still seal the circumferential gap between the second radially extending segments of the adjacent two rotor outer ring segments in a one-to-one correspondence; metal The sealing ring 301 cooperates with the radial sealing baffles 302 and the circumferential sealing baffles 303, so that even in a hot working state, the impinging cooling gas in the cold air cavity will not leak.

In the example of the present invention, the auxiliary sealing ring 301 is made of metal material, and the surface is plated with silver to prevent sintering in a high temperature environment. The axial width of each circumferential sealing baffle groove 208 is greater than the axial distance between the two second radially extending segments on the outer wall of each rotor outer ring segment. Each radial sealing baffle slot 207 should extend at least from the radial top end of the second radially extending section to the radial bottom end thereof. The radial sealing baffles 302 and the circumferential sealing baffles 303 between the outer ring segments of the rotors are made of high-temperature alloys to prevent damage in a high temperature environment.

The above-mentioned combined high-pressure turbine rotor outer ring cooling and sealing structure of the present invention can effectively prevent extrusion deformation of the high-pressure turbine rotor outer ring caused by thermal stress concentration in the working state by setting the high-pressure turbine rotor outer ring 2 as a split structure. The split high-pressure turbine rotor outer ring is radially located between the combustion outdoor casing 1 and the main flow passage of high temperature gas, preventing direct contact between the high temperature gas and the combustion outdoor casing 1, and protecting the combustion outdoor casing 1. Each lobe of the outer ring 2 of the high pressure turbine rotor is provided with a fixed number, and the relative position to the outer casing 1 of the combustion chamber is fixed. The installation and disassembly process are carried out in sequence, and the disassembly and assembly are simple and reliable. The outer casing 1 of the combustion chamber is provided with an impact cooling hole 104 in the circumferential direction, and the impact cooling is performed on the outer ring 2 of the high-pressure turbine rotor. efficiency. The impingement cooling gas is led out from the outlet of the high pressure compressor, and the bleed air path is short and the loss along the way is small. The gas velocity at the entrance of the impinging cooling hole is close to the speed of sound, and its flow rate can be determined by the cross-sectional area of the cooling hole. By adjusting the cross-sectional area of the hole, the amount of cold air impacting the outer ring of the rotor can be precisely controlled, and then the thermal deformation of the outer ring of the rotor can be precisely controlled to ensure that the outer ring of the high-pressure turbine rotor does not overheat and rotates, and the stator deforms in harmony. In order to make the impact cooling more effective, a card slot and a sealing baffle are arranged between each two rotor outer ring segments in the radial and circumferential directions to block and guide the cooling and sealing gas to prevent The cooling gas leaks through the gap between the two lobes, so that the axial and circumferential coverage of the cooling gas is higher, and the cooling effect is better. A high-temperature-resistant metal sealing ring is used between the combustion outdoor casing 1 and the high-pressure turbine rotor outer ring 2, which prevents the mainstream high-temperature gas from contacting the combustion outdoor casing through the gap between the two. The cooling gas inside the cooling cavity formed by the casing is effectively sealed to ensure that all the cold air is located in the cavity for cooling. The inner wall surface of the outer ring of the high-pressure turbine rotor is coated with a high-temperature wear-resistant coating to prevent the blades from being damaged when the high-pressure turbine rotor blades and the outer ring of the high-pressure turbine rotor are scraped due to too small clearance.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the present invention. within the range.

Claims (11)

1. A combined high-pressure turbine rotor outer ring cooling sealing structure, comprising a combustion outdoor casing, a high-pressure turbine rotor outer ring and an auxiliary sealing structure, and the high-pressure turbine rotor outer ring is assembled and arranged in the outer casing of the combustion chamber. On the inner wall, the auxiliary sealing structure is assembled between the outer casing of the combustion chamber and the outer ring of the high-pressure turbine rotor. The radially inner space of the outer ring of the high-pressure turbine rotor is a high-temperature gas channel, and the high-temperature gas channel There are high-pressure turbine rotor blades evenly distributed along the circumferential direction, characterized in that: The outer casing of the combustion chamber includes a casing casing with an integral ring structure, and at least two annular L-shaped corner structures with axial spacing and parallel arrangement are arranged on the inner wall of the casing casing. The corner directions of the annular L-shaped corner structures are the same, and each of the annular L-shaped corner structures includes a first radial extension section and a first axial extension section, and the first axial extension section is located at the the end of the first radially extending section; and at least one row of impingement cooling distributed in the circumferential direction is also provided on the casing of the casing located between the two adjacent annular L-shaped corner structures in the axial direction. holes, the impingement cooling holes are used to introduce impingement cooling gas; The outer ring of the high-pressure turbine rotor has a split structure as a whole, including a plurality of arc-shaped rotor outer ring segments, and at least two arc-shaped inverted rings with axial spacing and parallel arranged on the outer wall of each of the rotor outer ring segments are provided. L-shaped corner structures, the corner directions of each of the arc-shaped inverted L-shaped corner structures are the same, and each of the arc-shaped inverted L-shaped corner structures includes a second radial extension section and a second axial extension section, the second axially extending segment is disposed on the sidewall of the second radially extending segment, and there is a radial distance between the second axially extending segment and the end of the second radially extending segment; Each of the rotor outer ring segments is assembled and arranged on each of the annular L-shaped corner structures of the combustion outdoor casing through the arc-shaped inverted L-shaped corner structures provided on the outer wall thereof in a one-to-one correspondence; In the assembled state, the inner wall of the second axially extending section is fitted on the outer wall of the first axially extending section, and the end of the second radially extending section abuts against the casing shell On the inner wall of the rotor, and the axial space between the two pairs of mutually matched corner structures is formed as a cold air cavity; in the assembled state, there is also a circumferential gap between the two adjacent rotor outer ring segments, and even in the heat The circumferential gap is still maintained in the working state; The auxiliary sealing structure includes an auxiliary sealing ring, a radial sealing baffle and a circumferential sealing baffle, wherein the outer wall of each second axially extending section and the inner wall of the casing shell A said auxiliary sealing ring is arranged in the radial clearance space between them; the circumferential two ends of each said rotor outer ring segment are respectively provided with a circumferential sealing baffle card slot, and two adjacent rotor outer ring segments A said circumferential sealing blocking piece is arranged between two adjacent circumferential sealing blocking piece slots, and both ends of the circumferential sealing blocking piece are respectively movably inserted in the two circumferential sealing blocking pieces. Each of the circumferential sealing baffles can seal the circumferential gap between the walls of two adjacent rotor outer ring segments in a one-to-one correspondence, even in a hot working state; The circumferential ends of each of the second radially extending segments on the outer wall of each of the rotor outer ring segments are respectively provided with a radial sealing baffle card slot, and the adjacent two adjacent rotor outer ring segments are adjacent to each other. A radial sealing baffle is arranged between the two radial sealing baffles, and the two ends of the radial sealing baffle are respectively movably inserted in the two radial sealing baffles. In the slot, and even in a hot working state, each of the radial sealing baffles can still seal the circumferential direction between the second radially extending segments of two adjacent rotor outer ring segments in a one-to-one correspondence. Clearance; the auxiliary sealing ring works together with each of the circumferential sealing baffles and radial sealing baffles, so that even in a hot working state, the impact cooling gas in the cold air cavity will not leak ; An arc-shaped convex rib is arranged on the outer side wall of the second radially extending section near the upstream of each of the rotor outer ring segments, and in a hot working state, the arc-shaped convex rib is used to limit the high-pressure turbine The amount of movement along the axial direction of the rotor outer ring when it is heated and expanded and deformed; Each of the radial sealing baffle grooves should extend at least from the radial top end of the second radial extending section to the radial bottom end thereof. 2 . The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1 , wherein, in the high-pressure turbine rotor outer ring, each of the rotor outer ring segments starts from an angular zero point and runs in the same direction. 3 . The serial number is marked clockwise or counterclockwise, and is assembled according to the serial number during installation to ensure that the relative position of the casing and the combustion outdoor casing is fixed. 3. The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1, characterized in that, according to the temperature field distribution and strength checking results of the high-pressure turbine rotor outer ring working state, determine its split quantity. 4. The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1, characterized in that, a coating is provided on the inner wall of each of the rotor outer ring segments, and the coating is selected to withstand high temperature. wear material. 5 . The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 4 , wherein the hardness of the coating is lower than the hardness of the high-pressure turbine rotor blades, so as to ensure that under working conditions, both occurrences occur. 6 . During scraping, the high pressure turbine rotor blades are not damaged. 6 . The combined high-pressure turbine rotor outer ring cooling sealing structure according to claim 1 , wherein the auxiliary sealing ring is made of metal material, and its surface is silver-plated to prevent sintering in a high temperature environment. 7 . 7 . The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1 , wherein the axial width of each of the circumferential sealing baffles is larger than that of each of the rotor outer ring segments. 8 . The axial distance between the two second radially extending segments on the outer wall. 8 . The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1 , wherein the radial sealing baffles and the circumferential sealing baffles between the rotor outer ring segments are made of materials. 9 . High temperature alloy is selected to prevent damage in high temperature environment. 9 . The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1 , wherein, by adjusting the cross-sectional area of the impact cooling hole, the amount of cold air impacting the high-pressure turbine rotor outer ring is precisely controlled. 10 . , and then accurately control the thermal deformation of the outer ring of the high-pressure turbine rotor to ensure the coordinated deformation between the outer ring of the high-pressure turbine rotor and the outer casing of the combustion chamber, so that the tip of the high-pressure turbine rotor blade is connected to the outer ring of the high-pressure turbine rotor. The radial spacing between the rings is minimal, ensuring optimum aerodynamic performance. 10 . The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1 , wherein the impingement cooling gas introduced into the impingement cooling holes is led out from the outlet of the high-pressure compressor. 11 . 11 . The combined high-pressure turbine rotor outer ring cooling and sealing structure according to claim 1 , wherein the impingement cooling holes are uniformly distributed on the casing casing along the circumferential direction. 12 .

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