CN110847982B - Combined type cooling and sealing structure for outer ring of high-pressure turbine rotor - Google Patents
Combined type cooling and sealing structure for outer ring of high-pressure turbine rotor Download PDFInfo
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- CN110847982B CN110847982B CN201911064149.5A CN201911064149A CN110847982B CN 110847982 B CN110847982 B CN 110847982B CN 201911064149 A CN201911064149 A CN 201911064149A CN 110847982 B CN110847982 B CN 110847982B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a combined cooling and sealing structure of an outer ring of a high-pressure turbine rotor, which comprises a combustion chamber outer casing, a high-pressure turbine rotor outer ring and an auxiliary sealing structure, wherein the high-pressure turbine rotor outer ring is designed in a split mode, high-temperature resistant abradable coating is coated on the opposite surfaces of blades on the high-pressure turbine rotor outer ring, an impact cooling hole is formed in the combustion chamber outer casing along the circumferential direction, a cold air cavity is formed between the combustion chamber outer casing and the high-pressure turbine rotor outer ring by improving a connecting structure between the combustion chamber outer casing and the high-pressure turbine rotor outer ring, therefore, the high-efficiency cooling of the high-pressure turbine rotor outer ring is realized through cold air jet impact, and meanwhile, the heat load of a high-temperature component of the high-pressure turbine rotor outer ring is reduced by arranging the auxiliary sealing structures such as a sealing ring, a sealing baffle plate and the like to seal cold air, so that the thermal deformation of the component is controllable and the cold air consumption is reduced, and the cooling effect is maximized, and the stability and the reliability of the structure are improved.
Description
Technical Field
The invention relates to the field of aeroengines and gas turbines, in particular to improvement of a cooling and sealing structure of an outer ring of a high-pressure turbine rotor.
Background
The outer ring of the high-pressure turbine rotor is positioned at the downstream of the high-pressure turbine guider, is close to the outlet of the combustion chamber, is directly contacted with high-temperature fuel gas at the outlet of the combustion chamber, and is one of the parts with the highest temperature and the worst working conditions in the engine. For the outer ring of the high-pressure turbine rotor and the adjacent outer casing of the combustion chamber, on one hand, the environment temperature of the high-pressure turbine rotor can reach over 800 ℃, the inside of the high-pressure turbine rotor is mainstream high-temperature fuel gas, the outside of the high-pressure turbine rotor is outlet cold air of a high-pressure compressor, the temperature difference between the inside and the outside is large, and the absolute temperature is high. On the other hand, the structural size of the combustion chamber outer casing is large, and the thermal deformation is difficult to regulate and control.
The combustion chamber outer casing is usually integrally processed, the processing difficulty is high, the cost is high, and as a frame structure, the structure reliability is required to be ensured. Therefore, the combustion chamber outer casing is isolated and protected from direct contact with high-temperature gas. This function is typically accomplished by a high pressure turbine rotor outer ring located between the rotor blades and the combustor outer casing. The outer ring of the high-pressure turbine rotor is directly contacted with high-temperature gas, the temperature is high, the thermal stress is large, and the high-pressure turbine rotor needs to be efficiently cooled. The cooling design needs to be fine enough, the thermal deformation of the rotor and the stator is controllable, the rotor and the stator are coordinately deformed, and the gap between the tip of the rotor and the casing is as small as possible, so that the main flow aerodynamic loss is reduced. At the same time, the amount of air used for cooling should be guaranteed to be as small as possible, so as to improve the efficiency of the whole machine.
Existing high pressure turbine rotor outer ring designs generally fall into two categories. One design is a full ring integrated structure, which can be deformed due to excessive local extrusion stress under the condition of uneven heating. This deformation may be more pronounced under the influence of the large pressure differential inside and outside the outer ring of the high pressure turbine rotor. The whole-ring type high-pressure turbine rotor outer ring is damaged, needs to be replaced, and is high in cost and poor in maintainability. The other design is a split structure, but a large gap is left between the outer rings of every two high-pressure turbine rotors, and sealing is not performed, so that the gas consumption for cooling and sealing is large. Therefore, it is necessary to provide a novel cooling and sealing structure for the outer ring of the high-pressure turbine rotor and the adjacent outer casing of the combustor and the high-pressure turbine rotor blade, so as to achieve high maintainability, reduce the maintenance cost, control the thermal deformation of the hot end component, and reduce the amount of cold air.
Disclosure of Invention
Aiming at the technical requirements, the invention provides a combined type cooling and sealing structure for an outer ring of a high-pressure turbine rotor, which is characterized in that the outer ring of the high-pressure turbine rotor is designed in a split mode, high-temperature-resistant abradable coatings are coated on opposite surfaces of blades on the outer ring of the high-pressure turbine rotor, and an impact cooling hole is formed in a casing outside a combustion chamber along the circumferential direction, so that the outer ring of the high-pressure turbine rotor is efficiently cooled through cold air jet impact, and meanwhile, the sealing ring, a sealing separation blade and other auxiliary sealing structures are arranged to seal cold air, so that the heat load of a high-temperature part, namely the outer ring of the high-pressure turbine rotor, is reduced, the thermal deformation of the hot-end part is controllable, the amount of the cold air is reduced, the cooling effect is maximized, and the stability and the reliability of the structure are improved.
In order to achieve the technical aim, the technical scheme adopted by the invention is as follows:
a combined type cooling and sealing structure for an outer ring of a high-pressure turbine rotor comprises a combustion chamber outer casing, a high-pressure turbine rotor outer ring and an auxiliary sealing structure, wherein the high-pressure turbine rotor outer ring is assembled and arranged on the inner wall of the combustion chamber outer casing, the auxiliary sealing structure is assembled and arranged between the combustion chamber outer casing and the high-pressure turbine rotor outer ring, the radial inner side space of the high-pressure turbine rotor outer ring is a high-temperature gas channel, and high-pressure turbine rotor blades which are uniformly distributed along the circumferential direction are arranged in the high-temperature gas channel, the combined type cooling and sealing structure is characterized in that the combustion chamber outer casing comprises a casing shell which is of an integrated whole-ring structure, at least two annular L-shaped corner structures which have axial intervals and are arranged in parallel are arranged on the inner wall of the casing shell, the corner directions of the annular L-shaped corner structures are the same, and each annular L-shaped corner structure comprises a first radial extension section and a first axial extension section, the first axially extending section is located at an end of the first radially extending section; at least one row of impingement cooling holes distributed along the circumferential direction are further formed in the casing body axially between two adjacent annular L-shaped corner structures and used for introducing impingement cooling air;
the outer ring of the high-pressure turbine rotor is of a split structure integrally and comprises a plurality of arc-shaped rotor outer ring sections, at least two arc-shaped inverted-L-shaped corner structures which are axially spaced and arranged in parallel are arranged on the outer wall of each rotor outer ring section, the corner directions of the arc-shaped inverted-L-shaped corner structures are the same, each arc-shaped inverted-L-shaped corner structure comprises a second radial 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 a radial distance is reserved between the second axial extension section and the tail end of the second radial extension section; each rotor outer ring section is assembled and arranged on each annular L-shaped corner structure of the combustion chamber outer casing in a one-to-one correspondence mode through each arc-shaped inverted L-shaped corner structure arranged on the outer wall of the rotor outer ring section; when the cooling air cavity is in an assembling state, the inner wall of the second axial extension section is arranged on the outer wall of the first axial extension section in a matched mode, the tail end of the second radial extension section abuts against the inner wall of the casing body, and the axial space between the two pairs of corner structures which are matched with each other is formed into a cooling air cavity; when the rotor is in an assembly state, a circumferential gap is formed between two adjacent rotor outer ring sections, and the circumferential gap is still kept even in a thermal working state;
the auxiliary sealing structure comprises auxiliary sealing rings, radial sealing separation blades and circumferential sealing separation blades, wherein one auxiliary sealing ring is arranged in a radial clearance space between the outer wall of each second axial extension section and the inner wall of the casing body; the circumferential two ends of each rotor outer ring section are respectively provided with a circumferential sealing separation blade clamping groove, a circumferential sealing separation blade is arranged between two adjacent circumferential sealing separation blade clamping grooves of two adjacent rotor outer ring sections, the two ends of each circumferential sealing separation blade are respectively movably inserted into the two circumferential sealing separation blade clamping grooves, and each circumferential sealing separation blade can still seal circumferential gaps between the wall surfaces of the two adjacent rotor outer ring sections in a one-to-one correspondence manner even under a hot working state; the two ends of each second radial extension section on the outer wall of each rotor outer ring section are respectively provided with a radial sealing separation blade clamping groove, a radial sealing separation blade is arranged between two adjacent radial sealing separation blade clamping grooves of two adjacent rotor outer ring sections, the two ends of each radial sealing separation blade are respectively movably inserted into the two radial sealing separation blade clamping grooves, and each radial sealing separation blade can still seal a circumferential gap between the second radial extension sections of the two adjacent rotor outer ring sections in a one-to-one correspondence manner even under a hot working state; the metal sealing ring and each circumferential sealing separation blade and radial sealing separation blade act together, so that even in a hot working state, the impact cooling gas in the cooling gas cavity cannot be leaked.
In the cooling and sealing structure of the outer ring of the combined high-pressure turbine rotor, the high-pressure turbine rotor blades distributed in the circumferential direction are opposite parts of the outer ring of the high-pressure turbine rotor. The conventional outer ring of the high-pressure turbine rotor is a whole ring, and under the working condition, the local stress caused by uneven heating is usually overlarge. In the invention, the outer ring of the high-pressure turbine rotor is of a split structure, a circumferential gap is reserved between the outer ring sections of two adjacent split rotors, and the circumferential gap is larger during cold assembly, so that a certain circumferential gap is still reserved between the outer ring sections of the two adjacent split rotors in a hot working state (namely, when the temperature is highest), and the high-pressure turbine rotor cannot be deadlocked.
Preferably, in the high-pressure turbine rotor outer ring, each rotor outer ring segment is marked with a sequence number clockwise or anticlockwise by taking an angular zero point as a starting point, and is assembled according to the sequence number during installation, so that the relative position of the high-pressure turbine rotor outer ring and the combustor outer casing is ensured to be fixed.
Preferably, an arc-shaped rib is arranged on the outer side wall of the second radial extension section, close to the upstream, of each rotor outer ring section, and in a hot working state, the arc-shaped rib is used for limiting the axial movement of the high-pressure turbine rotor outer ring when the high-pressure turbine rotor outer ring is subjected to thermal expansion deformation.
Preferably, the number of the split is determined according to the temperature field distribution and the strength checking result of the high-pressure turbine rotor outer ring in the working state.
Preferably, a coating is arranged on the inner wall of each rotor outer ring section, and the coating is made of high-temperature-resistant and wearable materials. The coating material needs to be resistant to high temperature to prevent damage in high temperature environments.
Furthermore, the hardness of the coating is lower than that of the high-pressure turbine rotor blade, so that the high-pressure turbine rotor blade is not damaged when the high-pressure turbine rotor blade and the high-pressure turbine rotor blade are scraped and ground in a working state.
Preferably, the auxiliary sealing ring is made of a metal material with silver-plated surface, so that sintering in a high-temperature environment is prevented.
Preferably, the axial width of each circumferential sealing separation blade clamping groove is greater than the axial distance between two second radial extension sections on the outer wall of each rotor outer ring section.
Preferably, each of the radial sealing flap slots should extend at least from a radial top end to a radial bottom end of the second radially extending segment.
Preferably, the radial sealing separation blades and the circumferential sealing separation blades between the outer ring sections of the rotor are made of high-temperature alloy, so that damage to the rotor in a high-temperature environment is prevented.
Preferably, the sectional area of the impingement cooling hole is adjusted, so that the amount of cold air impinging on the outer ring of the high-pressure turbine rotor is accurately controlled, the thermal deformation amount of the outer ring of the high-pressure turbine rotor is further accurately controlled, the coordinated deformation between the outer ring of the high-pressure turbine rotor and the outer casing of the combustion chamber is ensured, the radial distance between the blade tip of the high-pressure turbine rotor blade and the outer ring of the high-pressure turbine rotor is minimized, and the optimal aerodynamic performance is ensured. Different hole patterns and hole inclination angles can be comprehensively selected, and the impact cooling effect is further improved.
Preferably, the impingement cooling gas introduced into the impingement cooling holes is led out from an outlet of the high pressure compressor.
Preferably, the impingement cooling holes are evenly distributed circumferentially on the casing shell.
Compared with the existing cooling and sealing structure for the outer ring of the high-pressure turbine rotor, the combined cooling and sealing structure for the outer ring of the high-pressure turbine rotor provided by the invention has the following advantages: 1. the outer ring of the high-pressure turbine rotor adopts a split structure, so that the extrusion deformation caused by thermal stress concentration in the working state is prevented. 2. The outer ring of the segmented high-pressure turbine rotor is radially positioned between the outer casing of the combustion chamber and the main flow channel of the high-temperature gas, so that the high-temperature gas is prevented from being in direct contact with the outer casing of the combustion chamber, and the outer casing of the combustion chamber is protected. 3. Each petal of the high-pressure turbine rotor outer ring is provided with a fixed number, and is fixed with the relative position of the combustion chamber outer casing, the installation and disassembly processes are carried out in sequence, the disassembly and the assembly are simple, and the reliability is high. 4. The outer ring of the high-pressure turbine rotor is subjected to impact cooling, so that the impact cooling efficiency is high, the cooling effect is good, the cold air consumption can be reduced under the same cooling effect, and the efficiency of the whole machine is improved. 5. The impingement cooling air is led out from the outlet of the high-pressure compressor, the air-entraining path is short, and the loss along the way is small. The gas velocity at the entrance of the impingement cooling holes is already close to sonic velocity and its flow can be determined by the cooling hole cross-sectional area. The sectional area in accessible regulation hole, accurate control strikes the cold air volume of rotor outer loop, and then the thermal deformation volume of accurate control rotor outer loop guarantees that high pressure turbine rotor outer loop does not overtemperature and commentaries on classics, stator coordinate the deformation. 6. For making impingement cooling more effective, on radial and two directions of circumference, arranged separation blade draw-in groove and the separation blade of obturating between the outer ring section of per two lamella rotors, block and the water conservancy diversion cooling obturating gas, prevent that cooling gas from leaking through the clearance between two lamellas, make cooling gas's axial, circumference coverage rate higher, the cooling effect is better. 7. The 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, so that mainstream high-temperature gas is prevented from contacting the outer casing of the combustion chamber through a gap between the outer casing of the combustion chamber and the high-pressure turbine rotor, and meanwhile, cooling gas in a cooling cavity formed by the outer ring of the high-pressure turbine rotor and the outer casing of the combustion chamber is effectively sealed, and all cooling gas is located in the cavity and used for cooling. 8. The inner wall of the outer ring of the high-pressure turbine rotor is coated with the high-temperature-resistant abradable coating, so that the blades are prevented from being damaged when the blades of the high-pressure turbine rotor and the outer ring of the high-pressure turbine rotor are scraped due to too small gaps.
Drawings
FIG. 1 is a schematic view of the outer ring cooling and sealing structure of the combined high pressure turbine rotor of the present invention;
FIG. 2 is a schematic view of the overall structure of the combustion chamber outer casing of the present invention;
FIG. 3 is a cross-sectional view of the combustion chamber outer casing of the present invention;
FIG. 4 is an enlarged partial cross-sectional view of the combustion chamber outer casing of the present invention;
FIG. 5 is a schematic view of the overall structure of the outer ring segment of the rotor according to the present invention;
FIG. 6 is a cross-sectional view of the outer ring segment of the rotor of the present invention;
FIG. 7 is a schematic view of the assembly of an auxiliary seal ring in the auxiliary seal structure of the present invention;
FIG. 8 is an assembly view of radial and circumferential sealing baffles in the auxiliary sealing structure of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1, the combined cooling and sealing structure for the outer ring of the high-pressure turbine rotor of the invention comprises an outer casing 1 of the combustion chamber, an outer ring 2 of the high-pressure turbine rotor and an auxiliary sealing structure 3, wherein the outer ring 2 of the high-pressure turbine rotor is assembled on the inner wall of the outer casing 1 of the combustion chamber, the auxiliary sealing structure 3 is assembled between the outer casing 1 of the combustion chamber and the outer ring 2 of the high-pressure turbine rotor, the radial inner space of the outer ring 2 of the high-pressure turbine rotor is a high-temperature gas channel, high-pressure turbine rotor blades 4 are uniformly distributed along the circumferential direction are arranged in the high-temperature gas channel, and the high-pressure turbine rotor blades 4 distributed along the circumferential direction are opposite parts of the outer ring 2 of the high-pressure turbine rotor.
As shown in fig. 2 to 4, in the outer ring cooling and sealing structure of the combined high-pressure turbine rotor of the present invention, the combustion chamber casing 1 includes a casing shell 101 having an integral whole ring structure, at least two annular L-shaped corner structures 102 having an axial distance and arranged in parallel are disposed on an inner wall of the casing shell 101, corner directions of the annular L-shaped corner structures 102 are the same, each annular L-shaped corner structure 102 includes a first radial extension section and a first axial extension section, and the first axial extension section is located at a terminal of the first radial extension section; at least one row of impingement cooling holes 104 uniformly distributed along the circumferential direction are further arranged on the casing body 101 axially between two adjacent annular L-shaped corner structures 102, the impingement cooling holes 104 are used for introducing impingement cooling air, and the impingement cooling air introduced into the impingement cooling holes 104 is led out from an outlet of the high-pressure compressor.
In the embodiment of the invention, the sectional area of the impingement cooling hole 104 is adjusted to accurately control the amount of cold air impinging on the outer ring of the high-pressure turbine rotor, so as to accurately control the thermal deformation amount of the outer ring 2 of the high-pressure turbine rotor, ensure the coordinated deformation between the outer ring 2 of the high-pressure turbine rotor and the outer casing 1 of the combustion chamber, minimize the radial distance between the blade tips of the high-pressure turbine rotor blades 4 and the outer ring 2 of the high-pressure turbine rotor, and ensure the optimal aerodynamic performance. In addition, different hole patterns and hole inclination angles can be comprehensively selected, and the impact cooling effect is further improved.
The conventional outer ring of the high-pressure turbine rotor is a whole ring, and under the working condition, the local stress caused by uneven heating is usually overlarge. In the combined type cooling and sealing structure for the outer ring of the high-pressure turbine rotor, the outer ring of the high-pressure turbine rotor is of a split structure, a circumferential gap is reserved between the outer ring sections of two adjacent split rotors, and the circumferential gap is large during cold mounting, so that a certain circumferential gap is reserved between the outer ring sections of the two adjacent split rotors in a hot working state (namely, when the temperature is highest), and the outer ring sections of the two adjacent split rotors cannot be jacked. Specifically, as shown in fig. 5 and 6, in the present invention, the high-pressure turbine rotor outer ring 2 is integrally in a split structure, and includes a plurality of split arc-shaped rotor outer ring segments, at least two arc-shaped inverted L-shaped corner structures 203 that have an axial distance and are arranged in parallel are disposed on an outer wall of each rotor outer ring segment, corner directions of the arc-shaped inverted L-shaped corner structures 203 are the same, and each arc-shaped inverted L-shaped corner structure 203 includes a second radial extension section and a second axial extension section, the second axial extension section is disposed on a side wall of the second radial extension section, and a radial distance is provided between the second axial extension section and a terminal 201 of the second radial extension section; each rotor outer ring section is correspondingly assembled and arranged on each annular L-shaped corner structure 102 of the combustion chamber outer casing 1 one by one through each arc-shaped inverted L-shaped corner structure 203 arranged on the outer wall of each rotor outer ring section; in the assembled state, the inner wall 205 of the second axial extension section is arranged on the outer wall 103 of the first axial extension section in a matching manner, and the tail end 201 of the second radial extension section abuts against the inner wall of the casing shell 101, so that the axial space between two pairs of corner structures which are matched with each other is formed into a cold air cavity; when the rotor is in an assembling state, a circumferential gap is formed between two adjacent rotor outer ring sections, and the circumferential gap is still kept even in a hot working state.
In the embodiment of the invention, in the high-pressure turbine rotor outer ring 2, each rotor outer ring segment takes an angular zero point as a starting point and marks a sequence number clockwise or anticlockwise, the rotor outer ring segments are assembled according to the sequence number during installation, the relative positions of the rotor outer ring segments and a combustion chamber outer casing are ensured to be fixed, the assembly and disassembly processes are carried out in sequence, the disassembly and the assembly are simple, and the reliability is high.
In the embodiment of the present invention, an arc-shaped rib 204 is provided on the outer side wall of the second radially extending section near the upstream of each rotor outer ring section, and in the hot working state, the arc-shaped rib 204 is used to limit the axial movement of the high-pressure turbine rotor outer ring 2 when it is subjected to thermal expansion deformation.
In the embodiment of the invention, the number of the split is determined according to the temperature field distribution and the strength checking result of the working state of the outer ring of the high-pressure turbine rotor.
In the embodiment of the present invention, the inner wall of each rotor outer ring segment is provided with a coating 206, and the coating is made of high temperature and abrasion resistant material. The coating material needs to be resistant to high temperature to prevent damage in high temperature environments. The hardness of the coating 206 is lower than that of the high-pressure turbine rotor blade 4, so that the high-pressure turbine rotor blade 4 is not damaged when the high-pressure turbine rotor blade and the high-pressure turbine rotor blade are scraped and ground in a working state.
As shown in fig. 7 and 8, in the cooling and sealing structure of the combined high-pressure turbine rotor outer ring, 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 disposed in a radial gap space between an outer wall of each second axial extension section and an inner wall of the casing housing 101; circumferential two ends of each rotor outer ring section are respectively provided with a circumferential sealing separation blade clamping groove 208, a circumferential sealing separation blade 303 is arranged between two adjacent circumferential sealing separation blade clamping grooves 208 of two adjacent rotor outer ring sections, two ends of the circumferential sealing separation blade 303 are respectively movably inserted into the two circumferential sealing separation blade clamping grooves 208, and even in a hot working state, each circumferential sealing separation blade 303 can still seal circumferential gaps between wall surfaces of the two adjacent rotor outer ring sections in a one-to-one correspondence manner; a radial sealing separation blade clamping groove 207 is respectively arranged at two circumferential ends of each second radial extension section on the outer wall of each rotor outer ring section, a radial sealing separation blade 302 is arranged between two adjacent radial sealing separation blade clamping grooves 207 of two adjacent rotor outer ring sections, two ends of the radial sealing separation blade 302 are respectively movably inserted into the two radial sealing separation blade clamping grooves 207, and even in a hot working state, each radial sealing separation blade 302 can still seal circumferential gaps between the second radial extension sections of the two adjacent rotor outer ring sections in a one-to-one correspondence manner; the metal sealing ring 301, the radial sealing baffle plates 302 and the circumferential sealing baffle plates 303 act together, so that even in a hot working state, the impact cooling gas in the cooling gas cavity cannot be leaked.
In the embodiment of the present invention, the auxiliary sealing ring 301 is made of a metal material, and the surface of the auxiliary sealing ring is plated with silver to prevent sintering in a high temperature environment. The axial width of each circumferential sealing baffle clamping groove 208 is larger than the axial distance between two second radial extending sections on the outer wall of each rotor outer ring section. Each radial sealing flap slot 207 should extend from at least the radial top end of the second radially extending segment to the radial bottom end thereof. The radial sealing separation blades 302 and the circumferential sealing separation blades 303 between the outer ring sections of the rotors are made of high-temperature alloy, so that damage to the rotor in a high-temperature environment is prevented.
According to the combined type cooling and sealing structure for the outer ring of the high-pressure turbine rotor, the outer ring 2 of the high-pressure turbine rotor is of the split structure, so that the extrusion deformation of the outer ring of the high-pressure turbine rotor caused by thermal stress concentration in a working state can be effectively prevented. The outer ring of the split high-pressure turbine rotor is radially positioned between the outer casing 1 of the combustion chamber and the main flow channel of the high-temperature gas, so that the high-temperature gas is prevented from being in direct contact with the outer casing 1 of the combustion chamber, and the outer casing 1 of the combustion chamber is protected. Each petal of the high-pressure turbine rotor outer ring 2 is provided with a fixed number, and the petal is fixed relative to the combustion chamber outer casing 1, the installation and disassembly processes are carried out in sequence, the disassembly and the assembly are simple, and the reliability is high. The outer casing 1 of the combustion chamber is provided with the impingement cooling holes 104 along the circumferential direction to perform impingement cooling on the outer ring 2 of the high-pressure turbine rotor, so that the impingement cooling efficiency is high, the cooling effect is good, the cold air consumption can be reduced under the same cooling effect, and the efficiency of the whole machine is improved. The impingement cooling air is led out from the outlet of the high-pressure compressor, the air-entraining path is short, and the loss along the way is small. The gas velocity at the entrance of the impingement cooling holes is already close to sonic velocity and its flow can be determined by the cooling hole cross-sectional area. The sectional area in accessible regulation hole, accurate control strikes the cold air volume of rotor outer loop, and then the thermal deformation volume of accurate control rotor outer loop guarantees that high pressure turbine rotor outer loop does not overtemperature and commentaries on classics, stator coordinate the deformation. For making impingement cooling more effective, in radial and two directions of circumference, arranged card groove and the separation blade of obturating between per two lamella rotor outer ring sections, stop and the water conservancy diversion cooling obturating gas, prevent that cooling gas from leaking through the clearance between two lamellas, make cooling gas's axial, circumference coverage rate higher, the cooling effect is better. A high-temperature-resistant metal sealing ring is used between the outer combustion chamber casing 1 and the outer high-pressure turbine rotor ring 2, so that mainstream high-temperature gas is prevented from contacting the outer combustion chamber casing through a gap between the outer combustion chamber casing and the high-pressure turbine rotor ring, meanwhile, cooling gas in a cooling cavity formed by the outer high-pressure turbine rotor ring and the outer combustion chamber casing is effectively sealed, and all cooling air is located in the cavity and used for cooling. The high-temperature-resistant abradable coating is coated on the inner side wall surface of the outer ring of the high-pressure turbine rotor, and the blades are prevented from being damaged when the blades of the high-pressure turbine rotor and the outer ring of the high-pressure turbine rotor are scraped due to too small gaps.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, but rather as the subject matter of any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention.
Claims (11)
1. A combined type cooling and sealing structure for an outer ring of a high-pressure turbine rotor comprises an outer casing of a combustion chamber, an outer ring of the high-pressure turbine rotor and an auxiliary sealing structure, wherein the outer ring of the high-pressure turbine rotor is assembled and arranged on the inner wall of the outer casing of the combustion chamber, the auxiliary sealing structure is assembled and arranged between the outer casing of the combustion chamber and the outer ring of the high-pressure turbine rotor, the radial inner space of the outer ring of the high-pressure turbine rotor is a high-temperature gas channel, and high-pressure turbine rotor blades which are uniformly distributed along the circumferential direction are arranged in the high-temperature gas channel,
the combustion chamber outer casing comprises a casing shell in an integral whole-ring structure, at least two annular L-shaped corner structures which have axial intervals and are arranged in parallel are arranged on the inner wall of the casing shell, the corner directions of the annular L-shaped corner structures are the same, each annular L-shaped corner structure comprises a first radial extension section and a first axial extension section, and the first axial extension section is positioned at the tail end of the first radial extension section; at least one row of impingement cooling holes distributed along the circumferential direction are further formed in the casing body axially between two adjacent annular L-shaped corner structures and used for introducing impingement cooling air;
the outer ring of the high-pressure turbine rotor is of a split structure integrally and comprises a plurality of arc-shaped rotor outer ring sections, at least two arc-shaped inverted-L-shaped corner structures which are axially spaced and arranged in parallel are arranged on the outer wall of each rotor outer ring section, the corner directions of the arc-shaped inverted-L-shaped corner structures are the same, each arc-shaped inverted-L-shaped corner structure comprises a second radial 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 a radial distance is reserved between the second axial extension section and the tail end of the second radial extension section; each rotor outer ring section is assembled and arranged on each annular L-shaped corner structure of the combustion chamber outer casing in a one-to-one correspondence mode through each arc-shaped inverted L-shaped corner structure arranged on the outer wall of the rotor outer ring section; when the cooling air cavity is in an assembling state, the inner wall of the second axial extension section is arranged on the outer wall of the first axial extension section in a matched mode, the tail end of the second radial extension section abuts against the inner wall of the casing body, and the axial space between the two pairs of corner structures which are matched with each other is formed into a cooling air cavity; when the rotor is in an assembly state, a circumferential gap is formed between two adjacent rotor outer ring sections, and the circumferential gap is still kept even in a thermal working state;
the auxiliary sealing structure comprises auxiliary sealing rings, radial sealing separation blades and circumferential sealing separation blades, wherein one auxiliary sealing ring is arranged in a radial clearance space between the outer wall of each second axial extension section and the inner wall of the casing body; the circumferential two ends of each rotor outer ring section are respectively provided with a circumferential sealing separation blade clamping groove, a circumferential sealing separation blade is arranged between two adjacent circumferential sealing separation blade clamping grooves of two adjacent rotor outer ring sections, the two ends of each circumferential sealing separation blade are respectively movably inserted into the two circumferential sealing separation blade clamping grooves, and each circumferential sealing separation blade can still seal circumferential gaps between the wall surfaces of the two adjacent rotor outer ring sections in a one-to-one correspondence manner even under a hot working state; the two ends of each second radial extension section on the outer wall of each rotor outer ring section are respectively provided with a radial sealing separation blade clamping groove, a radial sealing separation blade is arranged between two adjacent radial sealing separation blade clamping grooves of two adjacent rotor outer ring sections, the two ends of each radial sealing separation blade are respectively movably inserted into the two radial sealing separation blade clamping grooves, and each radial sealing separation blade can still seal a circumferential gap between the second radial extension sections of the two adjacent rotor outer ring sections in a one-to-one correspondence manner even under a hot working state; the auxiliary sealing ring and each circumferential sealing baffle and radial sealing baffle act together, so that impact cooling air in the cold air cavity cannot be leaked even in a hot working state;
an arc-shaped convex rib is arranged on the outer side wall of a second radial extension section, close to the upstream, of each rotor outer ring section, and in a thermal state working state, the arc-shaped convex rib is used for limiting the axial movement of the high-pressure turbine rotor outer ring when the high-pressure turbine rotor outer ring is subjected to thermal expansion deformation;
each radial sealing baffle clamping groove at least extends from the radial top end of the second radial extension section to the radial bottom end of the second radial extension section.
2. The combined high-pressure turbine rotor outer ring cooling and sealing structure as claimed in claim 1, wherein each of the rotor outer ring segments in the high-pressure turbine rotor outer ring is marked with a sequence number clockwise or counterclockwise with an angular zero point as a starting point, and is assembled according to the sequence number during installation, so as to ensure that the relative position of the high-pressure turbine rotor outer ring and the combustor outer casing is fixed.
3. The combined high-pressure turbine rotor outer ring cooling and sealing structure as claimed in claim 1, wherein the number of segments is determined according to the temperature field distribution and strength checking result in the working state of the high-pressure turbine rotor outer ring.
4. The combined high pressure turbine rotor outer ring cooling and sealing structure of claim 1, wherein a coating is disposed on an inner wall of each rotor outer ring segment, and the coating is made of a high temperature resistant and abradable material.
5. The combined high-pressure turbine rotor outer ring cooling and sealing structure as claimed in claim 4, wherein the hardness of the coating is lower than that of the high-pressure turbine rotor blade, so as to ensure that the high-pressure turbine rotor blade is not damaged when the high-pressure turbine rotor blade and the high-pressure turbine rotor blade are scraped under a working state.
6. The combined high-pressure turbine rotor outer ring cooling and sealing structure as claimed in claim 1, wherein the auxiliary sealing ring is made of a metal material, and the surface of the auxiliary sealing ring is plated with silver to prevent sintering in a high-temperature environment.
7. The combined high-pressure turbine rotor outer ring cooling and sealing structure as claimed in claim 1, wherein an axial width of each circumferential sealing baffle slot is greater than an axial distance between two second radially extending sections on an outer wall of each rotor outer ring section.
8. The combined type high-pressure turbine rotor outer ring cooling and sealing structure as claimed in claim 1, wherein the radial sealing separation blades and the circumferential sealing separation blades between the outer ring sections of the rotor are made of high-temperature alloy, so as to prevent damage in a high-temperature environment.
9. The combined type high-pressure turbine rotor outer ring cooling and sealing structure as claimed in claim 1, wherein a cooling air amount impacting on the high-pressure turbine rotor outer ring is precisely controlled by adjusting a sectional area of the impact cooling hole, so as to precisely control a thermal deformation amount of the high-pressure turbine rotor outer ring, thereby ensuring coordinated deformation between the high-pressure turbine rotor outer ring and a combustion chamber outer casing, minimizing a radial distance between a blade tip of the high-pressure turbine rotor blade and the high-pressure turbine rotor outer ring, and ensuring optimal aerodynamic performance.
10. The combined high pressure turbine rotor outer ring cooling and sealing structure of claim 1, wherein impingement cooling gas introduced into the impingement cooling holes is directed out of an outlet of a high pressure compressor.
11. The combined high pressure turbine rotor outer ring cooling seal structure of claim 1, wherein the impingement cooling holes are evenly distributed circumferentially on the casing shell.
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| CN201911064149.5A CN110847982B (en) | 2019-11-04 | 2019-11-04 | Combined type cooling and sealing structure for outer ring of high-pressure turbine rotor |
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| CN201911064149.5A CN110847982B (en) | 2019-11-04 | 2019-11-04 | Combined type cooling and sealing structure for outer ring of high-pressure turbine rotor |
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| CN110847982B true CN110847982B (en) | 2022-04-19 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111734500A (en) * | 2020-06-10 | 2020-10-02 | 山东鑫聚龙动力科技集团有限公司 | Sealing ring |
| CN113882910A (en) * | 2020-07-03 | 2022-01-04 | 中国航发商用航空发动机有限责任公司 | Turbine outer ring connection assembly, gas turbine engine and connection method |
| CN113638777B (en) * | 2021-09-10 | 2023-09-15 | 中国航发湖南动力机械研究所 | Turbine outer ring clamp, cooling structure of turbine outer ring, turbine and engine |
| CN117345433B (en) * | 2023-12-06 | 2024-02-06 | 成都中科翼能科技有限公司 | Sealing assembly component of gas turbine exhaust casing |
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| US6918743B2 (en) * | 2002-10-23 | 2005-07-19 | Pratt & Whitney Canada Ccorp. | Sheet metal turbine or compressor static shroud |
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| US9353649B2 (en) * | 2013-01-08 | 2016-05-31 | United Technologies Corporation | Wear liner spring seal |
| US9759081B2 (en) * | 2013-10-08 | 2017-09-12 | General Electric Company | Method and system to facilitate sealing in gas turbines |
| GB201322532D0 (en) * | 2013-12-19 | 2014-02-05 | Rolls Royce Plc | Rotor Blade Tip Clearance Control |
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| US5165847A (en) * | 1991-05-20 | 1992-11-24 | General Electric Company | Tapered enlargement metering inlet channel for a shroud cooling assembly of gas turbine engines |
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