CN115234377A - Engine high-low pressure turbine cooling structure with interstage support plate and method - Google Patents
Engine high-low pressure turbine cooling structure with interstage support plate and method Download PDFInfo
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- CN115234377A CN115234377A CN202210793093.2A CN202210793093A CN115234377A CN 115234377 A CN115234377 A CN 115234377A CN 202210793093 A CN202210793093 A CN 202210793093A CN 115234377 A CN115234377 A CN 115234377A
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- cavity
- bushing
- support plate
- cooling
- edge plate
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
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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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a cooling structure and a cooling method for a high-low pressure turbine of an engine with an interstage support plate, wherein the cooling structure comprises: the internal pipeline is arranged between a casing of the engine and the third lining and is used for introducing cooling air into a second cavity outside the bearing seat; the interstage support plate is arranged among the first bushing, the second bushing and the casing, a fifth cavity is formed among the interstage support plate and the casing, and a fourth cavity is formed among the interstage support plate, the first bushing and the second bushing; according to the invention, the interstage support plate, the internal pipeline and the third bushing are matched and sealed through parts, a design mode of bidirectional flow air entraining is formed among the internal passages of the support plate, the structure of the internal cavity of the support plate is more compact, the utilization rate of the internal passages of the interstage support plate is greatly improved, exhaust through the internal passages of the support plate is firstly used for cooling a plurality of transverse ribs arranged inside the interstage support plate and then directly exhausted from the engine case 1 to the outer duct of the engine through the fifth cavity, the thrust is increased, and the utilization efficiency of the engine air entraining is improved.
Description
Technical Field
The invention belongs to the technical field of turbine engines, and particularly relates to a cooling structure and a cooling method for a high-low pressure turbine of an engine with an interstage supporting plate.
Background
A conventional cooling and sealing air-entraining scheme for a high-pressure and low-pressure bearing of an engine through an interstage support plate is shown in figure 1, wherein one part of sealing air of a rear interstage of a high-pressure turbine is used for sealing a rear high-pressure plate, the other part of sealing air of the rear interstage of the high-pressure turbine is used for sealing an interstage bearing seat through a labyrinth, and is mixed with the air-entraining air from the interstage support plate through a right-side labyrinth of the bearing seat and used for sealing a front interstage of a low-pressure plate.
In a conventional technical scheme, along with the improvement of thermodynamic cycle parameters of an aircraft engine, particularly after the pressure ratio of a compressor reaches 24, high-pressure turbine disk rear sealing air needs to have high air entraining pressure which is about 0.8Mpa and the temperature of a corresponding air entraining position can reach 450 ℃, the air entraining air has temperature rise through a turbine disk core and a compressor disk cavity, if the high-temperature air is adopted to directly seal a bearing cavity, the overall temperature level of a bearing seat can be increased, a large heat load is brought to the work of the bearing, the normal use of the bearing is influenced, and meanwhile, lubricating oil in the bearing cavity generates a coking risk, and the normal work of the engine is influenced.
Disclosure of Invention
In view of the above problems, in one aspect, the present invention discloses an engine high-low pressure turbine cooling structure with an interstage support plate, the engine high-low pressure turbine including a first bushing, a second bushing and a third bushing, a first cavity being formed between the first bushing and the third bushing, and a third cavity being formed between the second bushing and the third bushing, the cooling structure including:
the internal pipeline is arranged between a casing of the engine and the third bushing and is used for introducing cooling air into a second cavity outside the bearing block;
the interstage support plate is arranged among the first bushing, the second bushing and the casing, a fifth cavity is formed among the interstage support plate and the casing, and a fourth cavity is formed among the interstage support plate, the first bushing and the second bushing;
the interstage support plate comprises an upper edge plate, a support plate and a lower edge plate, a fifth cavity is formed between the upper edge plate and the casing, a fourth cavity is formed between the lower edge plate and the first bushing and the second bushing, and the support plate is arranged between the upper edge plate and the lower edge plate and used for supporting and fixing the upper edge plate and the lower edge plate;
the internal pipeline sequentially penetrates through the casing, the upper edge plate, the lower edge plate and the third bushing and is inserted into the third cavity.
Furthermore, the bearing seat is arranged on the rotating base, one side of the rotating base, which faces the high-pressure turbine disc, is set as a high-pressure side, and one side of the rotating base, which faces the low-pressure turbine disc, is set as a low-pressure side;
two sides of the rotating base form dynamic seals with the third bushing through the first and third comb teeth respectively;
two sides of the bearing seat form dynamic seals respectively through the carbon seal and the space between the second grid tooth and the rotating base;
the space formed between the top of the bearing seat and the rotating base and the third bushing is defined as a second cavity.
Further, the second bushing and the third bushing on the high pressure side are connected with the first bushing through a first bolt, and the second bushing and the third bushing on the low pressure side are fixedly connected through a second bolt.
Furthermore, two paths of side branch mounting plates are arranged at the end part of the rotating base at the high-pressure side, and form dynamic seal with the first bushing and the third bushing through brush seal and the first comb tooth respectively;
and a first cavity is formed between the two side branch mounting plates and the first bushing and the third bushing.
Furthermore, a sixth cavity is formed between the outer side of the first bushing on the high-pressure side and the high-pressure turbine disc, the sixth cavity is communicated with the first cavity through a brush seal, and the first cavity is communicated with the fourth cavity.
Further, the rotating base on the low-pressure side is fixedly connected with the low-pressure turbine disc through a bolt assembly;
a dynamic seal is formed between the low-pressure turbine disc and the second bushing through a fourth labyrinth;
and a seventh cavity is formed between the low-pressure turbine disc on the low-pressure side and the second bushing and the third bushing.
Furthermore, openings are formed in the middle of the upper edge plate and the lower edge plate, the two sides of the top of the upper edge plate are clamped with the casing, and the two sides of the bottom of the lower edge plate are respectively connected with the first bushing and the second bushing;
the support plate is of an annular structure, the head end and the tail end of the annular structure are respectively fixedly connected with the upper edge plate and the lower edge plate, a support plate cavity is formed between the support plate and the upper edge plate, and the fourth cavity is communicated with the fifth cavity through the support plate cavity.
Furthermore, a plurality of transverse ribs are arranged on the inner wall of the annular structure of the support plate.
Furthermore, the inner pipeline runs through the branch board cavity, and the top of inner pipeline is equipped with mounting flange, be used for with the inner pipeline with the cooperation of the outer wall surface of machine casket is connected, just the top of inner pipeline is equipped with the interface for receive the cooling gas that outside air supply carried.
Still further, the top of the internal pipeline and the inner wall of the mounting hole of the casing form contact sealing;
the bottom of the inner pipeline is conical, and the inner pipeline and the third bushing are matched to form conical surface sealing.
In another aspect, the invention also discloses a cooling method for the high-low pressure turbine of the engine with the interstage support plate, which comprises the following steps:
an external air source feeds cooling air into the internal pipeline through a connector;
cooling air passes through the internal pipeline and enters the second cavity to act on the surface of the bearing seat, so that surface air blowing cooling is performed;
part of the cooling gas passes through the second cavity and acts on the bearing cavity to seal the bearing cavity;
the other part of the cooling gas passes through the second cavity and enters the seventh cavity to seal the space between the front stages of the low-pressure turbine disc;
and the other part of the cooling gas also passes through the second cavity, enters the first cavity, is mixed with the high-temperature airflow flowing into the first cavity from the sixth cavity, and is discharged to an engine outer duct through the fourth cavity and the fifth cavity in sequence.
Compared with the prior art, the invention has the beneficial effects that:
1) Parts among the interstage support plate, the internal pipeline and the third bushing are matched and sealed, so that a design mode of bidirectional flow air entraining is formed among internal channels of the support plate, the structure of an inner cavity of the support plate is more compact, and the utilization rate of the internal channel of the interstage support plate is greatly improved;
2) The cooling and sealing requirements of the bearing seat below the hot end component are met in a mode of separately introducing a cooling gas from the outside, the heat load of the bearing seat below the hot end component is effectively reduced, and the normal work of an engine bearing is ensured; the brush seal and the first grid tooth form a pressure relief and exhaust mode of the first cavity, so that the pressure of the first cavity is lower than that of the sixth cavity and the second cavity, and the risks of large bearing heat load, oil coking, high-temperature oil rising and the like caused by the fact that high-temperature seal gas of the sixth cavity directly enters the bearing cavity after the high-pressure plate are effectively inhibited;
3) Exhaust (a small amount of mixed gas of high-temperature air leaked from the sixth cavity and cooling gas of the first cavity) through the internal channel of the support plate is firstly used for cooling the interstage guider (a plurality of transverse ribs arranged on the inner cavity wall of the support plate) and then directly discharged from the casing to the outer duct of the engine through the fifth cavity, so that thrust is increased, and the utilization efficiency of engine bleed air is improved.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 illustrates a high and low pressure inter-turbine bearing cooling structure according to the prior art;
FIG. 2 illustrates a schematic diagram of a high and low pressure inter-turbine bearing cooling configuration according to an embodiment of the present invention;
FIG. 3 illustrates a schematic view of an interstage plate of the cooling structure according to an embodiment of the invention;
fig. 4 shows a schematic airflow direction diagram of a cooling structure of a bearing between a high pressure turbine and a low pressure turbine according to an embodiment of the invention.
In the drawings: 1. a casing; 2. an internal pipe; 3. an upper edge plate; 4. a support plate; 5. a lower flange plate; 6. a first bushing; 7. a second bushing; 8. a third bushing; 9. a low pressure turbine disk; 10. a high pressure turbine disc; 11. a bearing seat; 12. rotating the base; 13. sealing with carbon; 14. a first comb tooth; 15. a second comb tooth; 16. a third comb tooth; 17. a fourth comb tooth; 18. brushing and sealing; 19. a first chamber; 20. a second chamber; 21. a third chamber; 22. a fourth chamber; 23. a fifth chamber; 24. a sixth chamber; 25. a seventh chamber; 26. an O-shaped sealing ring; 27. a first bolt; 28. a second bolt; 29. an interface.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides an engine high-low pressure turbine cooling structure with an interstage support plate, the engine high-low pressure turbine comprises a first bushing 6, a second bushing 7 and a third bushing 8, a first cavity 19 is formed between the first bushing 6 and the third bushing 8, a third cavity 21 is formed between the second bushing 7 and the third bushing 8, and the cooling structure comprises an internal pipeline 2 and the interstage support plate. The internal pipeline 2 is arranged between the casing 1 and the third bushing 8 of the engine and is used for introducing cooling air into the second cavity 20 outside the bearing seat 11; the interstage support plate is arranged among the first bushing 6, the second bushing 7 and the casing 1, a fifth cavity 23 is formed among the interstage support plate and the casing 1, and a fourth cavity 22 is formed among the first bushing 6 and the second bushing 7; the interstage support plate comprises an upper edge plate 3, a support plate 4 and a lower edge plate 5, a fifth cavity 23 is formed between the upper edge plate 3 and the casing 1, a fourth cavity 22 is formed between the lower edge plate 5 and the first bushing 6 and the second bushing 7, and the support plate 4 is arranged between the upper edge plate 3 and the lower edge plate 5 and used for supporting and fixing the upper edge plate 3 and the lower edge plate 5; the internal pipe 2 is inserted into the third chamber 21 through the casing 1, the upper edge plate 3, the lower edge plate 5 and the third bushing 8 in sequence.
Referring to fig. 2, the bearing seat 11 is disposed on a rotating base 12, a side of the rotating base 12 facing the high-pressure turbine disk 10 is set as a high-pressure side, and a side facing the low-pressure turbine disk 9 is set as a low-pressure side; two sides of the rotating base 12 form dynamic seals with the third bushing 8 through the first and third comb teeth 14 and 16, respectively; two sides of the bearing seat 11 form dynamic seals with the rotating base 12 through a carbon seal 13 and a second labyrinth 15 respectively; the space defined between the top of the bearing housing 11 and the rotating base 12 and the third bushing 8 defines a second chamber 20.
The second bushing 7 and the third bushing 8 on the high pressure side are connected to the first bushing 6 by a first bolt 27, and the second bushing 7 and the third bushing 8 on the low pressure side are fixedly connected by a second bolt 28. Two paths of side branch mounting plates are arranged at the end part of the rotating base 12 at the high-pressure side, and dynamic seals are formed between the brush seals 18 and the first grid comb 14 and the first lining 6 and the third lining 8 respectively; a first cavity 19 is formed between the two side branch mounting plates and the first bushing 6 and the third bushing 8.
A sixth cavity 24 is formed between the outer side of the first bushing 6 on the high pressure side and the high pressure turbine disc 10, the sixth cavity 24 is communicated with the first cavity 19 through the brush seal 18, and the first cavity 19 is communicated with the fourth cavity 22. The rotating base 12 on the low-pressure side is fixedly connected with the low-pressure turbine disc 9 through a bolt assembly; a dynamic seal is formed between the low-pressure turbine disc 9 and the second bushing 7 through a fourth labyrinth 17; a seventh cavity 25 is formed between the low pressure turbine disc 9 on the low pressure side and the second and third bushings 7, 8.
It should be noted that the brush seal 18 can effectively reduce the leakage flow of the high-temperature air in the sixth cavity 24 to the first cavity 19, reduce the temperature of the blended gas, create favorable conditions for cooling the support plate 4, and meanwhile, the air discharged to the outer duct mainly comes from a position with lower pressure, so that the influence on the performance of the whole machine is reduced, the pressure of the second cavity 20 is ensured to be higher than that of the first cavity 19 through the first labyrinth 14 and the pressure relief exhaust, the air in the first cavity 19 does not flow back into the second cavity 20, and the pressure difference margin is ensured to exist between the first cavity 19 and the second cavity 20 in design. In addition, the carbon seal 13 uses materials including a flexible graphite sealing material, a reinforced graphite sealing material, and a carbon fiber composite material. Based on the self-lubricating property and the heat resistance of the carbon sealing material, the carbon sealing material is widely applied to the aerospace field. For example, the sealing material can replace some asbestos materials and rubber sealing materials applied to the aerospace field, high-strength graphite sealing rings applied to turbine pumps of aerospace engines and the like.
Referring to fig. 2, the brush seal 18 is fixedly installed at the bottom of the first bushing 6, and is a stationary member, the corresponding rotating base 12 is a rotating member, and a runway is provided on a side mounting plate of the rotating base 12, forming a dynamic seal with the brush seal 18. The first, second and third grates 14, 15 and 16 are respectively mounted on the rotating base 12 and are used for being matched with structural members respectively corresponding to the first, second and third grates 14, 15 and 16 to form a dynamic seal. Further, the low-pressure turbine disc 9 and the rotating base 12 are fixed through a bolt assembly, that is, the low-pressure turbine disc 9 and the rotating base 12 are both rotating parts, and the fourth labyrinth 17 is installed on the low-pressure turbine disc 9 and forms a dynamic seal with the third bushing 8.
In one embodiment of the invention, the sealing air quantity between front static stages of the low-pressure rotor (the low-pressure turbine disk 9) is controlled by two third labyrinth teeth 16 and four labyrinth teeth 17 with different radial heights, and a double-labyrinth-tooth sealing design is adopted, so that even if one of the labyrinth teeth fails to seal (the gap is large), the other labyrinth tooth can ensure that the sealing air quantity between the front stages of the low-pressure rotor is at a proper level, and the phenomenon that the sealing air quantity between the front stages of the low-pressure rotor is too large due to the failure of the labyrinth teeth, the cavity pressure of the second cavity 20 is greatly reduced, and the high-temperature air behind the high-pressure turbine disk 10 is filled into a bearing cavity is prevented.
Referring to fig. 3, an opening is formed in the middle of the upper edge plate 3 and the lower edge plate 5, two sides of the top of the upper edge plate 3 are clamped with the casing 1, and two sides of the bottom of the lower edge plate 5 are connected with the first bushing 6 and the second bushing 7 respectively; the support plate 4 is of an annular structure, the head end and the tail end of the annular structure are respectively fixedly connected with the upper edge plate 3 and the lower edge plate 5, a support plate cavity is formed between the support plate 4 and the upper edge plate 3 as well as between the support plate 4 and the lower edge plate 5, and the fourth cavity 22 and the fifth cavity 23 are communicated with each other through the support plate cavity. And a plurality of transverse ribs are arranged on the inner wall of the annular structure of the support plate 4.
In one embodiment of the present invention, the support plate 4, the upper edge plate 3 and the lower edge plate 5 are integrally formed in a one-piece casting manner, which can effectively improve the structural stability. The internal pipeline 2 penetrates through the branch plate cavity, the air inlet direction of the cooling air is conveyed to the bottom along the top of the internal pipeline 2, the mixed air of the cooling air and the high-temperature air is conveyed to the fifth cavity 23 from the fourth cavity 22 along the outer wall of the internal pipeline 2 during air exhaust, and the air conveying directions during air inlet and air exhaust are opposite. The bidirectional bleed air flowing structure of the interstage support plate enables bleed air and pressure relief exhaust in the support plate 4 to be isolated from each other and not to be affected with each other, increases the compactness of the support plate 4, and greatly improves the utilization rate of an internal channel of the interstage support plate.
Specifically, in the cooling process, the pressure and the temperature of the sixth cavity 24 are highest, the pressure and the temperature of the second cavity 20 are lower than those of the sixth cavity 24, the pressure of the first cavity 19 is effectively reduced through a pressure relief technology, and the pressure of the first cavity 19 is lower than those of the sixth cavity 24 and the second cavity 20, so that the air of the sixth cavity 24 and the air of the second cavity 20 are mixed in the first cavity 19 and are discharged to the engine exhaust duct through the support plate 4. The channel between the interstage support plate inner wall and the bleed pipeline directly discharges the mixed gas of the first cavity 19 to the outer duct, so that the thrust of the engine can be increased, the pressure of the first cavity 19 can be reduced, direct contact between high-temperature high-pressure sealing gas at the rear stage of the high-pressure turbine disc 10 and the bearing seat 11 and entering the bearing cavity can be prevented, the effects of cooling the bearing seat 11 and sealing the bearing cavity by the bleed low-temperature low-pressure cooling gas can be realized, and the effect of inhibiting the high-temperature air from directly entering the bearing cavity after the high-pressure turbine disc 10 can be realized.
Referring to fig. 2, a mounting flange is arranged at the top of the internal pipeline 2, and is used for connecting the internal pipeline 2 with the outer wall surface of the casing 1 in a matching manner, and a connector 29 is arranged at the top of the internal pipeline 2 and is used for receiving cooling air conveyed by an external air source. The top of the internal pipeline 2 and the inner wall of the mounting hole of the casing 1 form contact sealing; the bottom of the inner pipeline 2 is conical, and the bottom of the inner pipeline is matched with the third lining 8 to form conical surface sealing.
In one embodiment of the present invention, a circle of first grooves are formed on the inner pipeline 26 mm below the mounting flange, and are used for mounting an O-ring 26 to be matched and sealed with the casing 1, so as to prevent air in the fifth cavity 23 from leaking to the outside; the bottom of the inner pipeline 2 is conical, conical surface sealing is formed between the inner pipeline and the third lining 8, a second groove used for installing an O-shaped sealing ring 26 is arranged at the position 6mm above the bottommost part of the conical surface, and the second groove is matched and sealed with the third lining 8, so that air between the fourth cavity 22 and the third cavity 21 is isolated. During assembly, the internal pipeline 2 is directly inserted into the bottom of the conical sealing hole of the third bushing 8 through a mounting opening preset on the casing 1.
In another aspect, the present invention provides a method for cooling an engine high and low pressure turbine with an interstage support plate, the method comprising:
an external gas source feeds cooling gas into the internal pipeline 2 through a connector 29;
cooling air passes through the inner pipe 2 into the second cavity 20 and acts on the surface of the bearing seat 11 to perform surface blowing cooling;
part of the cooling gas passes through the second cavity 20 and acts on the bearing cavity to seal the bearing cavity;
another part of the cooling gas passes through the second cavity 20 and enters the seventh cavity 25 to seal the space between the front stages of the low-pressure turbine disc 9;
another part of the cooling air also passes through the second cavity 20, enters the first cavity 19, is mixed with the high-temperature air flow flowing into the first cavity 19 from the sixth cavity 24, and is discharged to the external bypass of the engine through the fourth cavity 22 and the fifth cavity 23 in sequence.
Referring to fig. 4, specifically, low-temperature (about 200 ℃) cooling air flows to the second cavity 20 through the internal pipeline 2 for air-blast cooling of the surface of the bearing seat 11, a part of air flow is used for sealing a bearing cavity through the carbon seal 13 and the second labyrinth 15, bleed air on the right side of the bearing seat 11 leaks to a main flow passage through the third labyrinth 16 and the fourth labyrinth 17 for sealing a front static stage of the low-pressure turbine, the first cavity 19 is communicated with the fourth cavity 22, and the fourth cavity 22 is communicated with the fifth cavity 23 through a passage formed between the pipeline and the inner wall of the support plate 4.
In order to realize that a cooling gas is led independently to seal a bearing cavity and inhibit high-temperature air from flowing into the bearing cavity after the high-pressure turbine disc 10, a first cavity 19 and a second cavity 20 are separated by brush type sealing, and the cooling gas is led from the outside to enter an internal pipeline 2; and then enters the second cavity 20 for cooling and sealing the bearing cavity, and the pressure of the cavity is reduced to inhibit high-temperature air in the sixth cavity 24 from directly entering the bearing cavity by the technology of pressure relief and air exhaust of the first cavity 19. Meanwhile, the pressure relief gas in the first cavity 19 is subjected to enhanced flow heat exchange through the inner cavity of the support plate 4 to cool the support plate 4, and then is directly discharged to an engine bypass through an exhaust port on the casing 1 to increase the thrust.
According to the technical scheme, on the premise that the sealing of the rear stage of the high-pressure turbine meets the requirement, a cooling gas is led out through the internal pipeline 2 arranged in the support plate 4 to cool the bearing seat 11, the sealed bearing cavity and the low-pressure front stage to be sealed, a pressure relief first cavity 19 is formed through the brush seal 18 and the first labyrinth 14, and the sealed gas and the cooling gas with higher temperature of the rear stage of the high-pressure turbine are discharged through a channel between the inner wall of the support plate 4 and the gas introducing pipeline.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (11)
1. An engine high and low pressure turbine cooling structure with an interstage support plate, the engine high and low pressure turbine comprising a first liner (6), a second liner (7) and a third liner (8), a first cavity (19) being formed between the first liner (6) and the third liner (8), and a third cavity (21) being formed between the second liner (7) and the third liner (8), the cooling structure being characterized by comprising:
the internal pipeline (2) is arranged between the casing (1) and the third lining (8) of the engine, and is used for introducing cooling air into a second cavity (20) outside the bearing seat (11);
the interstage support plate is arranged among the first bushing (6), the second bushing (7) and the casing (1), a fifth cavity (23) is formed among the interstage support plate and the casing (1), and a fourth cavity (22) is formed among the interstage support plate and the first bushing (6) and the second bushing (7);
the interstage support plate comprises an upper edge plate (3), a support plate (4) and a lower edge plate (5), a fifth cavity (23) is formed between the upper edge plate (3) and a casing (1), a fourth cavity (22) is formed between the lower edge plate (5) and a first bushing (6) and a second bushing (7), and the support plate (4) is arranged between the upper edge plate (3) and the lower edge plate (5) and used for supporting and fixing the upper edge plate (3) and the lower edge plate (5);
the internal pipeline (2) penetrates through the casing (1), the upper edge plate (3), the lower edge plate (5) and the third bushing (8) in sequence and is inserted into the third cavity (21).
2. The cooling structure according to claim 1, characterized in that the bearing housing (11) is provided on a rotating base (12), the side of the rotating base (12) facing the high-pressure turbine disk (10) being the high-pressure side and the side facing the low-pressure turbine disk (9) being the low-pressure side;
two sides of the rotating base (12) form dynamic seals with the third bushing (8) through a first comb tooth (14) and a third comb tooth (16) respectively;
two sides of the bearing seat (11) form dynamic seals with the rotating base (12) through a carbon seal (13) and a second grid tooth (15) respectively;
the space formed between the top of the bearing seat (11) and the rotating base (12) and the third bushing (8) is defined as a second cavity (20).
3. A cooling arrangement according to claim 2, characterised in that the side of the second bushing (7) facing the high pressure side and the third bushing (8) are connected to each other by means of a first bolt (27) and the first bushing (6), and that the second bushing (7) and the third bushing (8) on the low pressure side are fixedly connected by means of a second bolt (28).
4. The cooling structure according to claim 2, characterized in that two paths of side branch mounting plates are arranged at the end part of the rotating base (12) at the high pressure side, and dynamic seals are respectively formed between the brush seal (18) and the first grid section (14) and the first bushing (6) and the third bushing (8);
and a first cavity (19) is formed between the two branch mounting plates and the first lining (6) and the third lining (8).
5. A cooling arrangement according to claim 2, characterised in that a sixth chamber (24) is formed between the outside of the first bushing (6) on the high pressure side and the high pressure turbine disc (10), said sixth chamber (24) communicating with the first chamber (19) via the brush seal (18), and the first chamber (19) communicating with the fourth chamber (22).
6. The cooling structure according to claim 2, characterized in that the low pressure side rotating base (12) is fixedly connected with the low pressure turbine disk (9) by a bolt assembly;
a dynamic seal is formed between the low-pressure turbine disc (9) and the second lining (7) through a fourth comb tooth (17);
and a seventh cavity (25) is formed between the low-pressure turbine disc (9) on the low-pressure side and the second bushing (7) and the third bushing (8).
7. The cooling structure according to claim 1, characterized in that the middle of the upper edge plate (3) and the lower edge plate (5) is provided with an opening, the top two sides of the upper edge plate (3) are clamped with the casing (1), and the bottom two sides of the lower edge plate (5) are respectively connected with the first bushing (6) and the second bushing (7);
the support plate (4) is of an annular structure, the head end and the tail end of the annular structure are respectively fixedly connected with the upper edge plate (3) and the lower edge plate (5), a support plate cavity is formed between the support plate (4) and the upper edge plate (3) and between the support plate (4) and the lower edge plate (5), and the fourth cavity (22) and the fifth cavity (23) are communicated with each other through the support plate cavity.
8. The cooling structure according to claim 7, characterized in that the annular structure of the strip (4) is provided on its inner wall with transverse ribs.
9. The cooling structure according to claim 7, wherein the inner pipeline (2) penetrates through the branch plate cavity, and a mounting flange is arranged at the top of the inner pipeline (2) and is used for matching and connecting the inner pipeline (2) with the outer wall surface of the casing (1); and the top of the internal pipeline (2) is provided with a connector (29) for receiving cooling gas delivered by an external gas source.
10. A cooling structure according to any one of claims 1-9, characterized in that the top of the internal pipe (2) also forms a contact seal with the mounting bore inner wall of the casing (1);
the bottom of the internal pipeline (2) is conical, and the internal pipeline and the third bushing (8) are matched to form conical surface sealing.
11. A method of cooling an engine high and low pressure turbine with an interstage support plate, the method comprising:
an external air source leads cooling air into the internal pipeline (2) through a connector (29);
cooling air passes through the internal pipeline (2) and enters the second cavity (20) to act on the surface of the bearing seat (11) for surface air-blast cooling;
part of the cooling gas passes through the second cavity (20) and acts on the bearing cavity to seal the bearing cavity;
another part of the cooling gas passes through the second cavity (20) and enters a seventh cavity (25) to carry out pre-stage sealing on the low-pressure turbine disc (9);
and the other part of the cooling gas also passes through the second cavity (20), enters the first cavity (19), is mixed with the high-temperature gas flow flowing into the first cavity (19) from the sixth cavity (24), and then is discharged to the bypass of the engine through the fourth cavity (22) and the fifth cavity (23) in sequence.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210793093.2A CN115234377A (en) | 2022-07-05 | 2022-07-05 | Engine high-low pressure turbine cooling structure with interstage support plate and method |
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| CN202210793093.2A CN115234377A (en) | 2022-07-05 | 2022-07-05 | Engine high-low pressure turbine cooling structure with interstage support plate and method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115816071A (en) * | 2023-02-07 | 2023-03-21 | 成都中科翼能科技有限公司 | Assembly method of gas turbine supporting structure |
| CN117108374A (en) * | 2023-10-20 | 2023-11-24 | 中国航发沈阳发动机研究所 | Three-cavity separation type integrated bearing casing combined structure |
| CN117145593A (en) * | 2023-11-01 | 2023-12-01 | 中国航发沈阳发动机研究所 | Interactive air flow path multifunctional rear bearing casing structure |
-
2022
- 2022-07-05 CN CN202210793093.2A patent/CN115234377A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115816071A (en) * | 2023-02-07 | 2023-03-21 | 成都中科翼能科技有限公司 | Assembly method of gas turbine supporting structure |
| CN115816071B (en) * | 2023-02-07 | 2023-04-28 | 成都中科翼能科技有限公司 | Assembling method of gas turbine supporting structure |
| CN117108374A (en) * | 2023-10-20 | 2023-11-24 | 中国航发沈阳发动机研究所 | Three-cavity separation type integrated bearing casing combined structure |
| CN117108374B (en) * | 2023-10-20 | 2023-12-15 | 中国航发沈阳发动机研究所 | Three-cavity separation type integrated bearing casing combined structure |
| CN117145593A (en) * | 2023-11-01 | 2023-12-01 | 中国航发沈阳发动机研究所 | Interactive air flow path multifunctional rear bearing casing structure |
| CN117145593B (en) * | 2023-11-01 | 2024-01-02 | 中国航发沈阳发动机研究所 | Interactive air flow path multifunctional rear bearing casing structure |
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