A turbine disc core air entraining and temperature equalizing structure

Abstract

The application provides a turbine disc core air guide and temperature equalization structure, which comprises a turbine shaft spoke, a turbine disc, a first air guide hole on the front side of the turbine disc, a second air guide hole on the back side of the turbine disc, an air guide sleeve fixedly installed on the bottom side of the turbine disc, an air guide channel formed between the air guide sleeve and the bottom side of the turbine disc, a sealing ring fixedly installed on the turbine shaft spoke, and the sealing ring being connected to the air guide sleeve and being in sealed connection with the air guide sleeve. After the gas in the air system enters the turbine disc front cavity, the gas can flow into the turbine disc core cavity along the first air guide hole, then flow through the air guide channel between the air guide sleeve and the turbine disc, and then flow through the second air guide hole to the turbine disc back cavity, so that the turbine disc outer ring, the disc front, the disc core and the disc back are in the same gas source environment, thereby reducing the turbine disc radial temperature difference and the turbine disc axial temperature difference.

Description

Technical Field

[0001] This application belongs to the field of aero-engine and gas turbine technology, and specifically relates to a turbine disk core bleed air equalization structure. Background Technology

[0002] As the temperature at the turbine inlet continues to rise, the turbine rotor speed also continues to rise, and the strength problem of the turbine disk becomes more and more prominent. Among them, the thermal stress caused by the radial temperature difference due to the high temperature at the disk edge and the low temperature at the disk center, as well as the thermal stress caused by the temperature difference between the inlet and outlet of the disk, are among the main stresses borne by the turbine disk.

[0003] The turbine disk in the existing technology has a large temperature difference in the radial and axial directions, resulting in high turbine stress, which reduces the strength reserve of the turbine disk and poses a safety hazard to the use of the turbine rotor. Summary of the Invention

[0004] The purpose of this application is to provide a turbine disk core air bleed temperature equalization structure to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of this application is: a turbine disk core air bleed temperature equalization structure, comprising:

[0006] Turbine shaft spokes;

[0007] A turbine disk, wherein the front side of the turbine disk has a first air intake hole and the rear side of the turbine disk has a second air intake hole;

[0008] An air bleed sleeve fixedly installed on the bottom side of the turbine disk, forming an air bleed channel between the air bleed sleeve and the bottom side of the turbine disk; and

[0009] A sealing ring is fixedly installed on the turbine shaft spoke plate, and the sealing ring is connected to the bleed air sleeve and sealed to the bleed air sleeve;

[0010] After the gas in the air system enters the front cavity of the turbine disk, it can flow into the core cavity of the turbine disk along the first air intake hole, and then flow along the air intake channel between the air intake sleeve and the turbine disk, and flow into the rear cavity of the turbine disk through the second air intake hole, so that the outer ring, front, core and rear of the turbine disk are the same air source environment, thereby reducing the radial temperature difference and axial temperature difference of the turbine disk.

[0011] In some embodiments of this application, the upper side of the turbine shaft spoke is provided with a first grate tooth, which cooperates with the first honeycomb ring to form a sealing structure between the turbine disk front cavity and other chambers of the air system.

[0012] In some embodiments of this application, the front section of the turbine disk is provided with an L-shaped first mounting edge, the first air vent is provided on the axial extension of the first mounting edge, and the radial extension of the first mounting edge is provided with bolt holes. The turbine disk is fixedly connected to the turbine shaft spoke plate by a connector passing through the bolt holes.

[0013] In some embodiments of this application, the rear section of the turbine disk is provided with an axially extending mounting ring, the second air duct is disposed on the mounting ring, and the outer inner surface of the second air duct on the mounting ring is provided with an anti-rotation boss and a limiting screw outer mounting semicircular groove. The anti-rotation boss is used to achieve circumferential positioning of the turbine disk and the air duct sleeve with the anti-rotation boss mounting groove provided on the air duct sleeve. The limiting screw outer mounting semicircular groove is used to form a limiting screw mounting groove with the limiting screw inner mounting semicircular groove provided on the air duct sleeve. The limiting screw is disposed in the limiting screw mounting groove to achieve axial positioning of the turbine disk and the air duct sleeve.

[0014] In some embodiments of this application, the diameter of the limiting wire is smaller than the diameter of the limiting wire mounting groove, the front end of the limiting wire is provided with an insertion guide section, the rear end of the limiting wire is provided with a traction section, and the diameter of the guide section is smaller than the diameter of the traction section.

[0015] In some embodiments of this application, the front side of the air bleed sleeve is provided with circumferentially spaced air bleed support platforms, which overlap with the bottom of the turbine disk to form an air bleed channel between the air bleed sleeve and the bottom surface of the turbine disk. The rear side of the air bleed sleeve is bent to form an open insertion structure. The open insertion structure is provided with a semi-circular groove for mounting a limiting screw and an anti-rotation boss mounting groove. The mounting ring of the rear section of the turbine disk is inserted into the open insertion structure.

[0016] In some embodiments of this application, the outer side of the opening insertion structure is provided with a second grate, which cooperates with the second honeycomb ring to form a sealing structure between the turbine disk rear cavity and other chambers of the air system.

[0017] In some embodiments of this application, the front side of the sealing ring is provided with a radially extending second mounting edge, and the second mounting edge is provided with an axially extending third mounting edge. The second mounting edge is fixedly connected to the turbine shaft spoke plate through a connector, and the third mounting edge is provided with a sealing damping ring mounting groove. The sealing damping ring is installed in the sealing damping ring mounting groove and forms an overlapping damping structure with the bleed air sleeve to achieve a seal between the sealing ring and the bleed air sleeve.

[0018] In some embodiments of this application, a pressing surface is provided on the upper front end of the second mounting edge, and the pressing surface is axially pressed against the rear end face of the turbine shaft spoke plate to form a sealing structure between the turbine disk core cavity and other chambers of the air system.

[0019] In some embodiments of this application, a vent hole is provided on the upper side of the second mounting edge, and the vent hole is connected to a through hole provided on the turbine shaft spoke plate. At the same time, a fourth mounting edge is provided on the second mounting edge, and a graphite ring is provided on the fourth mounting edge to isolate the turbine disk core cavity from other chambers of the air system.

[0020] The turbine disk core air evacuation temperature equalization structure provided in this application can effectively reduce the radial and axial temperature differences of the turbine disk, reduce the thermal stress level of the turbine disk, and improve the strength reserve of the turbine disk. 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 typical turbine disk mounting structure.

[0023] Figure 2 This is a schematic diagram of the turbine disk core air duct temperature equalization structure of this application.

[0024] Figure 3 This is a schematic diagram of the turbine disk structure of this application.

[0025] Figure 4 This is a schematic diagram of the air bleed sleeve structure of this application.

[0026] Figure 5 This is a schematic diagram of the limiting wire structure of this application.

[0027] Figure 6 This is a schematic diagram of the sealing ring structure of this application.

[0028] Figure reference numerals: 100 - Typical turbine disk mounting structure; 101 - Turbine disk

[0029] 102-Precordial cavity

[0030] 103-Postdisc cavity

[0031] 104 - Core cavity; 200 - Turbine disk; Core air bleed temperature equalization structure; 210 - Turbine disk

[0032] 211-First Installation Side

[0033] 212- Bolt hole

[0034] 213-First air vent

[0035] 214-Mounting Ring

[0036] 215-Second air vent

[0037] 216-Anti-rotation boss

[0038] 217 - Limiting screw external mounting semi-circular groove; 220 - Air bleed sleeve

[0039] 221-Second Sealing of the Toothpick

[0040] 222-Anti-rotation boss mounting slot

[0041] 223 - Semicircular groove installed inside the limit screw; 224 - Air expiration support platform

[0042] 230-Limiting wire

[0043] 231-Introductory Section

[0044] 232-Traction Section

[0045] 240-Sealing Ring

[0046] 241-Second Installation Side

[0047] 242-Third Installation Side

[0048] 243- Bolt hole

[0049] 244-Compression Surface

[0050] 245-Ventilation port

[0051] 246-Sealing Damping Ring Mounting Groove

[0052] 247-Fourth Installation Side

[0053] 250-Turbine Shaft Spoke Plate

[0054] 260-Sealing Damping Ring

[0055] 270-First honeycomb ring

[0056] 280-Second honeycomb ring

[0057] 290-Graphite Ring Detailed Implementation

[0058] 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.

[0059] like Figure 1The diagram shows a typical turbine disk mounting structure 100 in the prior art. The turbine disk 101 has a front cavity 102, a rear cavity 103, and a center cavity 104. Each cavity is isolated, and their ambient temperatures differ significantly. If the temperature difference between the front cavity 102 and the rear cavity 103 is large, it will cause an unfavorable trend where one side of the turbine disk is "stretched" and the other side is "compressed," resulting in increased axial stress on the turbine disk. Similarly, the temperature difference between the center cavity 104 and the other cavities will also lead to increased radial stress. As the engine's operating conditions change, the tensile and compressive stresses will also change, making the use of the turbine disk even more unfavorable.

[0060] To address the thermal stress caused by radial and axial temperature differences in existing turbine disk mounting structures, this application provides a turbine disk core air duct temperature equalization structure, which makes the turbine disk structure more like an isothermal field design, effectively reducing the thermal stress caused by radial and axial temperature differences in the turbine disk.

[0061] like Figure 2 As shown, the turbine disk core bleed air equalization structure 200 provided in this application includes: turbine disk 210, bleed air sleeve 220, limiting wire 230, sealing ring 240, turbine shaft spoke plate 250, sealing damping ring 260, first honeycomb ring 270, second honeycomb ring 280 and graphite ring 290.

[0062] like Figure 3 As shown, the front section of the turbine disk 210 is provided with an L-shaped first mounting edge 211. The radial extension of the first mounting edge 211 is provided with bolt holes 212 for connecting with the turbine shaft spoke plate 220. The axial extension of the first mounting edge 211 is provided with a first air vent 213, which can introduce ambient air from the outside of the turbine disk into the center of the turbine disk.

[0063] The rear section of the turbine disk 210 is provided with an axially extending mounting ring 214. The mounting ring 214 has a second air duct 215, which can introduce ambient air from the disk core into the rear position of the turbine disk. The outer inner surface of the second air duct 215 on the mounting ring 214 has an anti-rotation boss 216, which can be interleaved with the anti-rotation boss mounting groove 222 on the air duct sleeve 220 to achieve circumferential anti-rotation function. Furthermore, the outer inner surface of the anti-rotation boss 216 on the mounting ring 214 has a semi-circular groove 217 for mounting the limiting screw, which can be used in conjunction with the inner mounting groove 223 and the limiting screw on the air duct sleeve 220 to achieve axial positioning of the air duct sleeve 220 and the turbine disk 210.

[0064] like Figure 4As shown, the front section (i.e., the left side) of the bleed air sleeve 220 is provided with circumferentially spaced bleed air support platforms 224, which can overlap with the bottom of the turbine disk to ensure that the bleed air sleeve 220 does not undergo large harmful deformation during operation. At the same time, it forms a bleed air channel between the bleed air sleeve 220 and the bottom surface of the turbine disk 210, thereby introducing bleed air from the disk core cavity into the disk rear cavity. The rear end of the bleed air sleeve 220 is bent to form an open insertion structure. This open insertion structure is provided with a semi-circular groove 223 for mounting a limiting wire, which has an oblique hole. The limiting wire 230 can be inserted through the oblique hole into the circular groove structure formed by the semi-circular groove 217 for mounting the limiting wire and the semi-circular groove 223 for mounting the limiting wire.

[0065] In this application, in order to facilitate the smooth insertion of the limiting wire 230, the limiting wire 230 can be divided into several segments according to the circumferential length, and the oblique hole positions are matched with the even distribution of the limiting wire 230.

[0066] The open plug structure is further provided with an anti-rotation boss mounting groove 222, which can be assembled with the anti-rotation boss 216 on the mounting ring 214 to realize the circumferential anti-rotation function of the turbine disk 210 and the bleed air sleeve 220.

[0067] In some embodiments of this application, the outer side of the opening plug structure is provided with a second sealing grate 221, which can form a sealing structure with the second honeycomb ring 280 to isolate the turbine disk rear cavity from other air system chambers.

[0068] like Figure 5 As shown, the diameter of the limiting wire 230 is slightly smaller than the diameter of the limiting wire mounting groove. Its front end is provided with a thinner insertion guide section 231, and its rear end is provided with a traction section 232, which can be used as a force position during assembly and disassembly.

[0069] like Figure 6 As shown, the sealing ring 240 has a radially extending second mounting edge 241 on its front side, and an axially extending third mounting edge 242 on the second mounting edge 241. The lower part of the second mounting edge 241 has a bolt hole 243 for connecting the sealing ring 240 and the turbine shaft spoke plate 250. The upper front end of the second mounting edge 241 has a pressing surface 244, which axially presses against the rear end face of the turbine shaft spoke plate 250 to prevent leakage of gas from the turbine disk core bleed and other air system chambers.

[0070] A sealing damping ring mounting groove 246 is provided at the rear end of the third mounting edge 242. The sealing damping ring 260 is set in the sealing damping ring mounting groove 246 and forms an overlapping damping structure with the inner ring surface of the bleed air sleeve 220. On the one hand, it can prevent the turbine disk bleed air from interacting and leaking with the gas in other air system chambers. On the other hand, it can reduce the harmful vibration of the thin-walled structure on the bleed air sleeve 220 and the sealing ring 240.

[0071] In some embodiments of this application, the sealing damping ring 260 may be made of rubber.

[0072] Furthermore, a vent 245 is provided on the upper side of the second mounting edge 241, and the vent 245 is connected to a through hole provided on the turbine shaft spoke plate 250. Based on this, a fourth mounting edge 247 is provided on the second mounting edge 241, which is approximately parallel to the third mounting edge 242. A graphite ring 290 is provided on the fourth mounting edge 247, which can isolate the turbine disk core cavity from other chambers of the air system.

[0073] After assembly, the air system flow path of the front cavity enters the core cavity from the first air inlet 213 on the front side of the turbine disk 210, and is discharged into the rear cavity through the second air inlet 215 on the rear side of the turbine disk 210 along the channel between the turbine disk 210 and the air duct sleeve 220. This achieves the same air source environment for the outer ring, core, front, and rear of the turbine disk, effectively reducing the radial and axial temperature differences of the turbine disk and lowering the thermal stress level of the turbine disk.

[0074] In some embodiments of this application, the upper side of the turbine shaft spoke 250 is provided with a first grating tooth, which cooperates with the first honeycomb ring 270 to isolate the turbine disk front cavity from other air system chambers.

[0075] The turbine disk core air evacuation temperature equalization structure provided in this application can effectively reduce the radial and axial temperature differences of the turbine disk, reduce the thermal stress level of the turbine disk, and improve the strength reserve of the turbine disk.

[0076] The structure of this application can be applied to low-pressure turbine disk structures, as well as other disk structures, including but not limited to high-pressure turbine disks. The structural scheme of this application can also be applied to the design of other air system chambers.

[0077] 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 turbine disk core air evacuation and temperature equalization structure, characterized in that, include: Turbine shaft spokes (250); Turbine disk (210), the front side of which has a first air intake hole (213) and the rear side of which has a second air intake hole (215); An air bleed sleeve (220) is fixedly installed on the bottom side of the turbine disk (210), and an air bleed channel is formed between the air bleed sleeve (220) and the bottom side of the turbine disk (210); as well as A sealing ring (240) is fixedly installed on the turbine shaft spoke plate (250), the sealing ring (240) is connected to the bleed air sleeve (220) and is sealed to the bleed air sleeve (220); After the gas in the air system enters the front cavity of the turbine disk, it can flow into the core cavity of the turbine disk through the first air vent (213), and then flow through the air venting channel between the air venting sleeve (220) and the turbine disk (210), and flow into the rear cavity of the turbine disk through the second air vent (215), so that the outer ring, front, core and rear of the turbine disk are the same air source environment, thereby reducing the radial temperature difference and axial temperature difference of the turbine disk.

2. The turbine disk core air duct temperature equalization structure as described in claim 1, characterized in that, The upper side of the turbine shaft spoke (250) is provided with a first grate tooth, which cooperates with the first honeycomb ring (270) to form a sealing structure between the turbine disk front cavity and other chambers of the air system.

3. The turbine disk core air evacuation and temperature equalization structure as described in claim 1, characterized in that, The front section of the turbine disk (210) is provided with an L-shaped first mounting edge (211), the first air vent (213) is provided on the axial extension of the first mounting edge (211), and the radial extension of the first mounting edge (211) is provided with bolt holes. The turbine disk (210) is fixedly connected to the turbine shaft spoke plate (250) by a connector passing through the bolt holes.

4. The turbine disk core air duct temperature equalization structure as described in claim 3, characterized in that, The rear section of the turbine disk (210) is provided with an axially extending mounting ring (214). The second air duct (215) is provided on the mounting ring (214). The outer inner surface of the second air duct (215) on the mounting ring (214) is provided with an anti-rotation boss (216) and a limiting screw outer mounting semi-circular groove (217). The anti-rotation boss (216) is used to achieve circumferential positioning of the turbine disk (210) and the air duct sleeve (220) with the anti-rotation boss mounting groove (222) provided on the air duct sleeve (220). The limiting screw outer mounting semi-circular groove (217) is used to form a limiting screw mounting groove with the limiting screw inner mounting semi-circular groove (223) provided on the air duct sleeve (220). The limiting screw (230) is provided in the limiting screw mounting groove to achieve axial positioning of the turbine disk (210) and the air duct sleeve (220).

5. The turbine disk core air bleed temperature equalization structure as described in claim 4, characterized in that, The diameter of the limiting wire (230) is smaller than the diameter of the limiting wire mounting groove. The front end of the limiting wire (230) is provided with an insertion guide section (231), and the rear end of the limiting wire (230) is provided with a traction section (232). The diameter of the guide section (231) is smaller than the diameter of the traction section (232).

6. The turbine disk core air bleed temperature equalization structure as described in claim 4, characterized in that, The front side of the air bleed sleeve (220) is provided with circumferentially spaced air bleed support platforms (224), which overlap with the bottom of the turbine disk to form an air bleed channel between the bottom surface of the air bleed sleeve (220) and the turbine disk (210). The rear side of the air bleed sleeve (220) is bent to form an open insertion structure. The open insertion structure is provided with a semi-circular groove (223) for installing the limiting screw and an anti-rotation boss mounting groove (222). The mounting ring (214) of the rear section of the turbine disk (210) is inserted into the open insertion structure.

7. The turbine disk core air bleed temperature equalization structure as described in claim 6, characterized in that, The outer side of the open plug structure is provided with a second grate tooth, which cooperates with the second honeycomb ring (280) to form a sealing structure between the turbine disk rear cavity and other chambers of the air system.

8. The turbine disk core air bleed temperature equalization structure as described in claim 1, characterized in that, The sealing ring (240) has a radially extending second mounting edge (241) on its front side, and an axially extending third mounting edge (242) on the second mounting edge (241). The second mounting edge (241) is fixedly connected to the turbine shaft spoke plate through a connector. The third mounting edge (242) is provided with a sealing damping ring mounting groove (246). The sealing damping ring (260) is installed in the sealing damping ring mounting groove (246) and forms an overlapping damping structure with the bleed air sleeve (220) to achieve a seal between the sealing ring (240) and the bleed air sleeve (220).

9. The turbine disk core air evacuation and temperature equalization structure as described in claim 8, characterized in that, The upper front end of the second mounting edge (241) is provided with a pressing surface (244), which is axially pressed against the rear end face of the turbine shaft spoke plate (250) to form a sealing structure between the turbine disk core cavity and other chambers of the air system.

10. The turbine disk core air bleed temperature equalization structure as described in claim 8 or 9, characterized in that, The upper side of the second mounting edge (241) is provided with a vent hole (245), which is connected to the through hole provided on the turbine shaft spoke plate (250). At the same time, a fourth mounting edge (247) is provided on the second mounting edge (241), and a graphite ring (290) is provided on the fourth mounting edge (247) to isolate the turbine disk core cavity from other chambers of the air system.

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