Counter-rotating turbine cooling structure

Abstract

The invention provides a contra-rotating turbine cooling structure, which belongs to the field of aero-engines and comprises a high-pressure turbine disc and high-pressure turbine blades mounted on the high-pressure turbine disc. The low-pressure turbine disc and the low-pressure turbine blades are arranged on the lower part of the low-pressure turbine disc; the low-pressure turbine disc is arranged on the low-pressure turbine shaft; the first flow guide ring is installed on the front side of the high-pressure turbine disc, a first cavity is formed between the first flow guide ring and the high-pressure turbine disc, and the second flow guide ring extends from the front side of the high-pressure turbine disc to the rear side of the high-pressure turbine disc along the bottom of the high-pressure turbine disc, and a second cavity is formed between the second flow guide ring and the high-pressure turbine disc. The third flow guide ring wraps the front side and the bottom side of the low-pressure turbine disc to form semi-surrounding surrounding, and therefore a third cavity is formed between the third flow guide ring and the low-pressure turbine disc. The bearing support ring is mounted on the low-pressure turbine shaft, and forms a fourth cavity with the high-pressure turbine disc and the third flow guide ring; and one part of the air entraining ring used for introducing cooling air enters the high-pressure turbine blade, and the other part of the air entraining ring enters the low-pressure turbine blade for cooling.

Description

Technical Field

[0001] This application belongs to the field of aero-engines, and specifically relates to a counter-rotating turbine cooling structure. Background Technology

[0002] Turbine components are crucial parts of aircraft engines. A traditional turbine component consists of a high-pressure turbine (1) and a low-pressure turbine (2), with guide vanes (3) positioned between them. Figure 1 As shown. Turbine components operate in a high-temperature environment and require bleed air from the compressor to cool them. The low-pressure turbine typically receives its cooling air from the guide vane assembly. However, to achieve a lightweight and compact design, a certain type of aero-engine has adopted a bladeless design for its turbine components—that is, eliminating the guide vanes. For bladeless turbine components, the structural form has changed drastically, rendering existing turbine cooling structures unsuitable.

[0003] Therefore, a turbine cooling structure suitable for bladeless turbines is needed to achieve turbine cooling. Summary of the Invention

[0004] The purpose of this application is to provide a counter-rotating turbine cooling structure to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of this application is: a counter-rotating turbine cooling structure, comprising:

[0006] High-pressure turbine disk and high-pressure turbine blades mounted on the high-pressure turbine disk;

[0007] A low-pressure turbine disk and low-pressure turbine blades mounted on the low-pressure turbine disk, the low-pressure turbine disk being mounted on a low-pressure turbine shaft;

[0008] The system comprises a first guide ring, a second guide ring, and a third guide ring. The first guide ring is installed on the front side of the high-pressure turbine disk, forming a first cavity between the first guide ring and the high-pressure turbine disk for introducing cooling gas into the high-pressure turbine blades. The second guide ring extends from the front side of the high-pressure turbine disk along the bottom to the rear side of the high-pressure turbine disk, forming a second cavity between the second guide ring and the high-pressure turbine disk. The third guide ring wraps around the front and bottom sides of the low-pressure turbine disk to form a semi-circular enclosure, thereby forming a third cavity between the third guide ring and the low-pressure turbine disk.

[0009] A bearing support ring is installed on the low-pressure turbine shaft, and the bearing support ring forms a fourth cavity with the high-pressure turbine disk and the third guide ring;

[0010] The bleed air ring is used to introduce cooling gas. Part of the cooling gas introduced through the bleed air ring enters the high-pressure turbine blades along the first cavity for cooling, and the other part of the cooling gas enters the low-pressure turbine blades along the second cavity, the fourth cavity and the third cavity for cooling.

[0011] In at least one embodiment of this application, a first vent hole is provided on the upper side of the high-pressure turbine disk, and a fifth vent hole is provided on the first guide ring. Cooling gas entering from the induced channel of the induced air ring enters the first cavity along the fifth vent hole and enters the high-pressure turbine blade along the first vent hole.

[0012] In at least one embodiment of this application, the fifth vent of the first guide ring and the air intake channel of the air intake ring are provided with a toothed sealing structure.

[0013] In at least one embodiment of this application, the high-pressure turbine disk has a support structure extending axially forward. The support structure is provided with a third vent hole and a second vent hole is provided on the rear side of the high-pressure turbine disk. Cooling gas entering from the priming channel of the priming ring can enter the second cavity along the third vent hole and flow from the second vent hole to the fourth cavity.

[0014] In at least one embodiment of this application, a first groove and a second groove are respectively provided on the upper and lower sides of the front end of the support structure, and the first guide ring and the second guide ring are respectively mounted on the support structure by a first elastic ring and a second elastic ring installed in the first groove and the second groove.

[0015] In at least one embodiment of this application, both the first elastic ring and the second elastic ring are open C-shaped structures.

[0016] In at least one embodiment of this application, the third guide ring is provided with a sixth vent hole, and the front side of the low-pressure turbine disk is provided with a fourth vent hole. Cooling gas flowing into the fourth cavity enters the third cavity along the sixth vent hole and enters the low-pressure turbine blades from the fourth vent hole for cooling.

[0017] In at least one embodiment of this application, the first guide ring, the second guide ring, the high-pressure turbine blade, the high-pressure turbine disk, the first elastic ring, and the second elastic ring constitute a high-pressure turbine rotor assembly, and the low-pressure turbine blade, the low-pressure turbine disk, the low-pressure turbine shaft, the third guide ring, and the bearing support ring constitute a low-pressure turbine rotor assembly. The high-pressure turbine rotor assembly is supported on the low-pressure turbine rotor assembly by a second bearing, and the low-pressure turbine rotor assembly is supported on the engine stator component by a first bearing.

[0018] In at least one embodiment of this application, the high-pressure turbine rotor assembly rotates in the opposite direction to the low-pressure turbine rotor assembly during operation.

[0019] In at least one embodiment of this application, the sixth vent hole is not axially arranged with the second vent hole, and the axial position of the sixth vent hole is closer to the rear side than that of the second vent hole.

[0020] Compared with traditional turbine components, this application eliminates the guide vane assembly and provides a guide vane-less counter-rotating turbine cooling structure, achieving a lightweight and compact design. Furthermore, the designed cold airflow path passes through the main components of the turbine, resulting in excellent cooling performance. Attached Figure Description

[0021] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0022] Figure 1 This is a schematic diagram of a traditional turbine structure.

[0023] Figure 2 This is a schematic diagram of the counter-rotating turbine cooling structure of this application.

[0024] Figure 3 This is a schematic diagram of the airflow path for the counter-rotating turbine cooling structure of this application. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0026] like Figure 1 The diagram shows a typical turbine component. A typical turbine component 100 includes a high-pressure turbine 101, a low-pressure turbine 102, and a guide vane 103 disposed between the high-pressure and low-pressure turbines. The guide vane 103 is a stator component. After a stream of cryogenic gas is introduced from the compressor, it passes radially through the guide vane 103 and is led out from the rear side of the turbine disk of the guide vane 103 and leads to the low-pressure turbine 102, thereby achieving cooling of the low-pressure turbine 102.

[0027] However, after removing the guide vane 201, the existing low-pressure turbine cooling air supply scheme is no longer applicable. Therefore, this application provides a counter-rotating turbine cooling structure to accommodate the counter-rotating turbine structure after removing the guide vane and to construct the cooling flow path.

[0028] like Figure 2As shown, the counter-rotating turbine cooling structure 200 provided in this application mainly includes: high-pressure turbine blades 201, high-pressure turbine disk 202, low-pressure turbine blades 203, low-pressure turbine disk 204, low-pressure turbine shaft 205, first bearing 2071, second bearing 2072, bleed air ring 208, first guide ring 2091, second guide ring 2092, third guide ring 2093 and bearing support ring 210.

[0029] In this application, both the high-pressure turbine blade 201 and the low-pressure turbine blade 203 are air-cooled blades. That is, both the high-pressure turbine blade 201 and the low-pressure turbine blade 203 have cooling channels inside and air film holes on the blade surface. Cooling gas entering the cooling channel flows out from the air film holes, thereby forming air film cooling on the blade surface, thus protecting the high-pressure turbine blade 201 and the low-pressure turbine blade 203.

[0030] The high-pressure turbine blade 201 and the low-pressure turbine blade 203 are connected to the high-pressure turbine disk 202 and the low-pressure turbine disk 204 respectively through a tenon and mortise structure. For example, the tenon and mortise structure can be a dovetail tenon or a circumferential fir tree tenon, and the type of tenon and mortise structure is determined according to the usage environment or operating conditions of the high-pressure turbine blade 201 and the low-pressure turbine blade 203.

[0031] The high-pressure turbine disk 202 includes an axially forward-extending support structure 2021. The upper front side, lower rear side of the high-pressure turbine disk 202, and the support structure 2021 are respectively provided with a first vent 2022, a second through hole 2023, and a third through hole 2024 for the flow of cold air. The high-pressure turbine disk 202 has a first grate 2025 and a second grate 2026 on both sides of the second through hole 2023 to seal the cold air flowing out of the second through hole 2023. The high-pressure turbine disk 202 has a first groove 2027 and a second groove 2028 on the upper and lower front sides of the support structure 2021 for installing a first elastic ring 2061 and a second elastic ring 2062. In this application, both the first elastic ring 2061 and the second elastic ring 2062 are open C-shaped structures, and their cross-sections are L-shaped, thereby forming a stop structure that mates with the first guide ring 2091 and the second guide ring 2092. The exemplary first elastic ring 2061 and the second elastic ring 2062 are typically made of an elastic metal material, such as spring steel.

[0032] The upper front side of the low-pressure turbine disk 204 is provided with a fourth vent 2041 for circulating cold air. The low-pressure turbine disk 204 is fixedly connected to the low-pressure turbine shaft 205 by bolts, and the low-pressure turbine shaft 205 is supported on the engine stator structure by the first bearing 2071.

[0033] The bleed air ring 208 is a stator component (i.e., it does not rotate during operation) and is fixedly connected to the engine stator components. The bleed air ring 208 has multiple sets of bleed air channels 2081 for introducing cool air to cool the turbine components. The bleed air channel 2071 has third grates 2082 on its front and rear sides to seal the gas flowing out of the bleed air channel 2081 and prevent leakage.

[0034] The first guide ring 2091 is located above and to the left of the high-pressure turbine disk 202 and is connected to the high-pressure turbine disk 202 via a first elastic ring 2061. The first guide ring 2091 has two sealing grates that engage with third grates 2082 to seal the cold air flowing in through the bleed air ring 208. Between the two sealing grates are multiple sets of fifth vent holes 2094 that engage with the bleed air passage 2081. A first cavity Q1 is formed between the first guide ring 2091 and the high-pressure turbine disk 202, which guides the cold air to the first vent hole 2022 on the high-pressure turbine disk 202, thereby cooling the high-pressure turbine blades 201.

[0035] The second guide ring 2092 is located below the high-pressure turbine disk 202, and its two ends are connected to the front and rear sides of the high-pressure turbine disk 202 respectively through the second elastic ring 2062. A second cavity B is formed between the second guide ring 2092 and the high-pressure turbine disk 202 for the flow of cooling air to the low-pressure turbine blades 203. A sealing ring 211 is provided between the second guide ring 2092 and the rear connection of the high-pressure turbine disk 202. In some embodiments of this application, the sealing ring 211 is a high-temperature resistant sealing ring. For example, the sealing ring 211 can be a graphite sealing ring or a silicone rubber seal, etc.

[0036] The third guide ring 2093 surrounds the front and bottom sides of the low-pressure turbine disk 204 to form a semi-circular enclosure, thereby creating a third cavity Q3 between the third guide ring 2093 and the low-pressure turbine disk 204. The third guide ring 2093 has multiple sets of sixth vent holes 2095 for the flow of cool air. The third guide ring 2093 and the bearing support ring 210 are fixedly connected to the low-pressure turbine shaft 205 by bolts. A fourth cavity Q4 is formed between the third guide ring 2093, the bearing support ring 210, and the high-pressure turbine disk 202. The second cavity Q2, the fourth cavity Q4, and the third cavity Q3 are in a connected state. The fourth cavity Q4 is provided with a grate sealing structure on both the front and rear sides. The grate sealing structure on the front side is composed of the honeycomb ring 2096 on the third guide ring 2093 and the first grate 2025. The grate sealing structure on the rear side is composed of the sealing track on the bearing support ring 210 and the second grate 2026.

[0037] The high-pressure turbine rotor assembly consists of a first guide ring 2091, a second guide ring 2092, a high-pressure turbine blade 201, a high-pressure turbine disk 202, a first elastic ring 2061, and a second elastic ring 2062. The low-pressure turbine rotor assembly consists of a low-pressure turbine blade 203, a low-pressure turbine disk 204, a low-pressure turbine shaft 205, a third guide ring 2093, and a bearing support ring 210. The high-pressure turbine rotor assembly is supported on the low-pressure turbine rotor assembly by a second bearing 2072, and the low-pressure turbine rotor assembly is supported on other engine components (such as the stator casing) by a first bearing 2071, thereby enabling the high-pressure and low-pressure turbine rotor assemblies to rotate independently.

[0038] In a preferred embodiment of this application, the high-pressure turbine rotor assembly rotates in the opposite direction to the low-pressure turbine rotor assembly.

[0039] like Figure 3 As indicated by the arrows, during operation, the cool air first flows from the bleed air passage 2081 on the bleed air ring 208 into the fifth vent 2094. At this time, the cool air is divided into two flow paths: one flows into the first cavity Q1, then through the first vent 2022 into the internal cooling passage of the high-pressure turbine blade 201, and finally into the main passage through the film cooling holes on the surface of the high-pressure turbine blade 201; the other flows into the cavity Q2 through the third vent 2024, then through the second vent 2023 into the fourth cavity Q4, then through the sixth vent 2095 into the third cavity Q3, then through the fourth vent 2041 into the internal cooling passage of the low-pressure turbine blade 203, and finally into the main passage through the film cooling holes on the surface of the low-pressure turbine blade 203.

[0040] In a preferred embodiment of this application, the sixth vent 2095 is not axially aligned with the second vent 2023. Compared to the second vent 2023, the axial position of the sixth vent 2095 is further back, so that after the cold air passes through the second vent 2023, the cold air flows from left to right, which can more effectively cool the cavity where the second bearing 2072 is located. After the cold air passes through the sixth vent 2095, the flow direction changes to right to left, which can more effectively cool the disk core of the low-pressure turbine disk 204.

[0041] Compared with traditional turbine components, this application eliminates the guide vane assembly and provides a guide vane-less counter-rotating turbine cooling structure, achieving a lightweight and compact design. Furthermore, the designed cold airflow path passes through the main components of the turbine, resulting in excellent cooling performance.

[0042] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A counter-rotating turbine cooling structure, characterized in that, include: High-pressure turbine disk and high-pressure turbine blades mounted on the high-pressure turbine disk; A low-pressure turbine disk and low-pressure turbine blades mounted on the low-pressure turbine disk, the low-pressure turbine disk being mounted on a low-pressure turbine shaft; The system comprises a first guide ring, a second guide ring, and a third guide ring. The first guide ring is installed on the front side of the high-pressure turbine disk, forming a first cavity between the first guide ring and the high-pressure turbine disk for introducing cooling gas into the high-pressure turbine blades. The second guide ring extends from the front side of the high-pressure turbine disk along the bottom to the rear side of the high-pressure turbine disk, forming a second cavity between the second guide ring and the high-pressure turbine disk. The third guide ring wraps around the front and bottom sides of the low-pressure turbine disk to form a semi-circular enclosure, thereby forming a third cavity between the third guide ring and the low-pressure turbine disk. A bearing support ring is installed on the low-pressure turbine shaft, and the bearing support ring forms a fourth cavity with the high-pressure turbine disk and the third guide ring; The bleed air ring is used to introduce cooling gas. Part of the cooling gas introduced through the bleed air ring enters the high-pressure turbine blades along the first cavity for cooling, and the other part of the cooling gas enters the low-pressure turbine blades along the second cavity, the fourth cavity and the third cavity for cooling.

2. The counter-rotating turbine cooling structure as described in claim 1, characterized in that, The high-pressure turbine disk is provided with a first vent hole on its upper side and a fifth vent hole on the first guide ring. Cooling gas entering from the induced channel of the induced air ring enters the first cavity along the fifth vent hole and then enters the high-pressure turbine blades along the first vent hole.

3. The counter-rotating turbine cooling structure as described in claim 2, characterized in that, The fifth vent of the first guide ring and the air intake channel of the air intake ring are provided with a toothed sealing structure on both sides.

4. The counter-rotating turbine cooling structure as described in claim 2, characterized in that, The high-pressure turbine disk has a support structure that extends axially forward. The support structure is provided with a third vent hole and a second vent hole is provided on the rear side of the high-pressure turbine disk. Cooling gas entering from the induced channel of the induced air ring can enter the second cavity along the third vent hole and flow from the second vent hole to the fourth cavity.

5. The counter-rotating turbine cooling structure as described in claim 4, characterized in that, The front end of the support structure is provided with a first groove and a second groove on its upper and lower sides, respectively. The first guide ring and the second guide ring are respectively installed on the support structure by a first elastic ring and a second elastic ring installed in the first groove and the second groove.

6. The counter-rotating turbine cooling structure as described in claim 5, characterized in that, Both the first elastic ring and the second elastic ring are open C-shaped structures.

7. The counter-rotating turbine cooling structure as described in claim 5, characterized in that, The third guide ring is provided with a sixth vent hole, and the front side of the low-pressure turbine disk is provided with a fourth vent hole. The cooling gas flowing into the fourth cavity enters the third cavity along the sixth vent hole and enters the low-pressure turbine blades through the fourth vent hole for cooling.

8. The counter-rotating turbine cooling structure as described in any one of claims 5 to 7, characterized in that, The first guide ring, the second guide ring, the high-pressure turbine blades, the high-pressure turbine disk, and the first and second elastic rings constitute a high-pressure turbine rotor assembly. The low-pressure turbine blades, the low-pressure turbine disk, the low-pressure turbine shaft, the third guide ring, and the bearing support ring constitute a low-pressure turbine rotor assembly. The high-pressure turbine rotor assembly is supported on the low-pressure turbine rotor assembly by a second bearing, and the low-pressure turbine rotor assembly is supported on the engine stator by a first bearing.

9. The counter-rotating turbine cooling structure as described in claim 8, characterized in that, The high-pressure turbine rotor assembly rotates in the opposite direction to the low-pressure turbine rotor assembly during operation.

10. The counter-rotating turbine cooling structure as described in claim 7, characterized in that, The sixth vent is not axially aligned with the second vent, and the axial position of the sixth vent is closer to the rear than that of the second vent.

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