An oil and gas separation engine turbine disk post cooling structure

Abstract

The application provides an oil-gas separation engine turbine disc rear cooling structure, which comprises a turbine disc, a rear baffle, a sealing ring assembly, a guide plate, a mounting bolt, a turbine shaft, a grid ring and a contact sealing assembly; the turbine disc is fixedly connected with the turbine shaft and the grid ring to form a rotor, and the guide plate and the sealing ring assembly are assembled together through the mounting bolt to form a stator; the turbine disc and the rear baffle and the sealing ring assembly form a disc rear cavity, the guide plate is located in the disc rear cavity and between the turbine disc and the sealing ring assembly, so that the cooling gas flowing into the turbine disc core and the lubricating oil leaking into the disc rear cavity through the contact sealing assembly are separated to form a separate cooling gas accelerating channel and a lubricating oil flow channel. The application can effectively separate the exhaust flow path and the lubricating oil flow path of the turbine disc rear cavity, prevent the leaked lubricating oil from directly contacting the high-temperature components of the turbine rotor, effectively reduce the temperature rise of the disc rear cavity airflow along the flow process, and improve the disc rear cooling effect.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to an engine turbine disk aftercooling structure with oil-gas separation. Background Technology

[0002] The turbine disks and baffles of advanced low-bypass turbofan engines operate in extremely harsh environments, typically enduring thermal loads from extreme temperature gradients and rotor centrifugal loads. The mounting edges also often contain stress concentration points such as holes and slots. To reduce stress on the turbine disk, cooling gas is usually introduced into the front and rear chambers to lower the temperature rise. The turbine disk core of low-bypass turbofan engines is typically designed with complex oil and gas chamber structures to ensure oil supply and return to the bearings and to ensure sealing.

[0003] like Figure 1 The diagram shows a typical turbine disk rear cavity cooling structure 10. The turbine disk 11, baffle 12, and turbine shaft 13 together form the rotor component, while the sealing ring 14 and casing form the stator component. The turbine disk 11 and sealing ring 14 form the rear cavity, which is quite large. Cooling gas enters the rear cavity through the vents behind the turbine disk, causing backflow and reducing the flow rate, thus affecting the cooling effect on the turbine disk surface. Simultaneously, the oil chamber and rear cavity use contact-type grate seals. During the transition state, lubricating oil leaks from the sealing assembly 15 between the rotor and the rear casing, remaining on the honeycomb structure. A small amount of lubricating oil leaks through the honeycomb structure into the rear cavity, directly contacting the hot-end rotor surfaces such as the turbine disk 11 and baffle 12, resulting in coking. Excessive coking degrades the surface quality of the turbine disk 11 and baffle 12. Especially during the transition state, the leakage of relatively cold lubricating oil into the hotter surfaces of the turbine disk 11 and baffle 12 can easily cause cracks in the rotor components. Summary of the Invention

[0004] The purpose of this application is to provide an oil-gas separation engine turbine disk aftercooling structure to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of this application is: an oil-gas separation engine turbine disk rear cooling structure, the disk rear cooling structure including: turbine disk, rear baffle, sealing ring assembly, guide plate, mounting bolts, turbine shaft, grate ring and contact sealing assembly;

[0006] The turbine disk is fixedly connected to the turbine shaft and the grate ring to form a rotor;

[0007] The guide plate and the sealing ring assembly are assembled together by mounting bolts to form a stator;

[0008] The turbine disk, the rear baffle, and the sealing ring assembly form a rear disk cavity. The guide plate is located in the rear disk cavity and between the turbine disk and the sealing ring assembly, thereby separating the cooling gas flowing into the turbine disk center from the lubricating oil leaking into the rear disk cavity through the contact sealing assembly, forming separate cooling gas acceleration channels and lubricating oil flow channels.

[0009] In a preferred embodiment of this application, the guide plate is a flexible thin-walled structure, thereby enabling the guide plate to have unloading and coordinated deformation capabilities. The flexible thin-walled structure profile and dimensions of the guide plate are determined according to the arc-shaped rotor wall shape formed by the turbine disk and the rear baffle. The spacing between the guide plate and the rotor is determined according to the deformation under the ultimate state of the rotor and stator.

[0010] In a preferred embodiment of this application, the guide plate has an inner mounting edge and an outer mounting edge. The inner mounting edge is assembled to the front side of the sealing ring assembly by mounting bolts. The outer mounting edge is a double-protrusion lace structure. The double-protrusion lace structure includes a first protrusion and a second protrusion arranged axially front and rear. The first protrusion and the second protrusion both have corresponding notches in the circumferential direction to form a lace structure.

[0011] In a preferred embodiment of this application, the first boss is closer to the turbine disk than the second boss, and the height of the first boss, which is closer to the turbine disk, is greater than the height of the second boss, which is farther away from the turbine disk.

[0012] In a preferred embodiment of this application, the outer diameter end of the sealing ring assembly is provided with a radially extending plug lace structure, and the plug lace structure is provided with a notch in the circumferential direction to form a lace structure;

[0013] The plug lace structure at the outer diameter end of the sealing ring assembly is inserted into the double boss lace structure on the outer mounting edge of the guide plate. The notch in the plug lace structure and the notch in the double boss lace structure are connected to form a ventilation groove, which serves as a pressure equalization channel between the guide plate and the sealing ring assembly.

[0014] In a preferred embodiment of this application, the outer diameter end of the sealing ring assembly is configured as an I-shaped end structure, and grooves are formed on both sides of the end structure to form an air passage bite seal with the rear baffle and the inner flow channel plate respectively.

[0015] The sealing ring assembly has an oil passage hole on the lower side of its end structure, through which leaked lubricating oil flows out from the lubricating oil flow channel.

[0016] In a preferred embodiment of this application, the inner diameter end of the sealing ring assembly is provided with an oil receiving groove. The axial length of the oil receiving groove is determined according to the assembly requirements of the mounting bolts and the farthest and closest positions of the oil throwing path of the grate ring. The oil receiving groove is provided with an oil leakage hole, which is used to allow the lubricating oil leaking through the contact sealing assembly to enter the lubricating oil flow channel of the rear cavity of the disc along the oil leakage hole.

[0017] In a preferred embodiment of this application, the inner diameter end of the toothed ring is provided with an axially inclined oil receiving ring with a solid ring structure. The end of the oil receiving ring has a notch pointing in the axial direction, and the end face of the notch at least partially overlaps with the end face of the contact sealing assembly.

[0018] The main body of the toothed ring has an oil slinger groove on the surface facing the turbine shaft. The lubricating oil leaking from the contact sealing assembly, collected by the oil receiving ring, flows along the oil slinger groove towards the oil receiving groove under the centrifugal force of the rotor.

[0019] In a preferred embodiment of this application, there are multiple oil-slinging grooves, which are evenly distributed in the circumferential direction.

[0020] In a preferred embodiment of this application, the cross-section of the oil slinger is designed with a large aspect ratio, which means that the circumferential width is greater than the axial depth.

[0021] The oil-gas separation engine turbine disk rear cooling structure provided in this application can effectively separate the exhaust flow path and lubricating oil flow path of the turbine disk rear cavity of aero-engines / gas turbines, preventing leaked lubricating oil from directly contacting the high-temperature components of the turbine rotor. At the same time, the separation structure is designed as a flexible conformal flow guide structure, which reduces the cross-sectional area of ​​the exhaust channel behind the disk, allowing the cooling airflow to be accelerated and uniformly cooled on the surface of the hot-end rotor components such as the disk and baffle. This effectively reduces the temperature rise of the airflow in the rear cavity along the flow process, improves the rear cooling effect, and enhances engine safety. Attached Figure Description

[0022] 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.

[0023] Figure 1 This is a schematic diagram of a typical turbine disk rear cavity cooling structure in the prior art.

[0024] Figure 2 This is a schematic diagram of the turbine disk rear cavity cooling structure of this application.

[0025] Figure 3 This is a schematic diagram of the outer mounting edge of the deflector in this application.

[0026] Figure 4 This is a schematic diagram showing the connection between the guide plate and the sealing ring assembly in this application.

[0027] Figure 5 This is a schematic diagram of the outer diameter end of the sealing ring assembly in this application.

[0028] Figure 6 This is a schematic diagram of the inner diameter end of the sealing ring assembly in this application.

[0029] Figure 7 This is a schematic diagram of the toothed ring structure in this application.

[0030] Figure 8 This is a schematic diagram of the oil-slinging groove of the toothed ring in this application.

[0031] Figure label:

[0032] 10 - Typical turbine disk rear chamber cooling structure

[0033] 11-Turbine disk

[0034] 12-baffle

[0035] 13-Turbine Shaft

[0036] 14-Sealing Ring

[0037] 15-Sealing Components

[0038] 20-Engine turbine disc aftercooler structure

[0039] 21-Turbine disk

[0040] 211-Ventilation Hole

[0041] 22-Rear bumper

[0042] 23-Sealing Ring Assembly

[0043] 231-Plug with decorative trim

[0044] 232-End Structure

[0045] 233-Oil passage hole

[0046] 234-Oil receiving tank

[0047] 235-Oil Leakage Hole

[0048] 24-Blower plate

[0049] 241-Double-bowl lace structure

[0050] 2411 - First Protrusion

[0051] 2412 - Second Protrusion

[0052] 2413-Gap

[0053] 25-Mounting bolts

[0054] 26-Turbine Shaft

[0055] 27-Fang tooth ring

[0056] 271-Oil receiving ring

[0057] 272-Block

[0058] 273-Oil slinger

[0059] 28-Contact sealing assembly

[0060] 29-Inner flow channel plate Detailed Implementation

[0061] 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.

[0062] like Figure 2 As shown, this application provides an engine turbine disk aftercooling structure 20 with oil-gas separation. The engine turbine disk aftercooling structure 20 mainly consists of a turbine disk 21, a rear baffle 22, a sealing ring assembly 23, a guide plate 24, mounting bolts 25, a turbine shaft 26, a toothed ring 27, a contact sealing assembly 28, and an inner flow channel plate 29.

[0063] The turbine disk 21, the rear baffle 22, and the sealing ring assembly 23 form a rear cavity. A guide plate 24 is provided in the rear cavity. The guide plate 24 is located between the turbine disk 21 and the sealing ring assembly 23. It is assembled with the sealing ring assembly 23 by mounting bolts 25 to form a stator, thereby separating the cooling gas flowing into the turbine disk center from the lubricating oil flow path that leaks into the rear cavity through the contact sealing assembly 28, forming a separate cooling gas acceleration channel and a lubricating oil flow channel.

[0064] The turbine disk 21 has an axially extending support arm that is connected to the turbine shaft 26. A toothed ring 27 is fitted on the other side of the turbine shaft 26. The toothed ring 27 and the sealing ring assembly 23 form a toothed sealing structure. The rear baffle 22 is snapped onto the turbine disk 21, so that it can rotate together with the turbine disk 21, the turbine shaft 26 and the toothed ring 27 to form a rotor.

[0065] In this application, the guide plate 24 is a flexible thin-walled structure, which enables it to have the ability to unload and coordinate deformation. The shape and size of the flexible thin-walled structure of the guide plate 24 are determined according to the arc-shaped rotor wall shape formed by the turbine disk 21 and the rear baffle 22. The gap between the guide plate 24 and the rotor is calculated based on the deformation of the rotor and stator under the limit state. The gap between the two is minimized while ensuring no risk of collision and wear, thereby increasing the flow velocity of the cooling gas.

[0066] The deflector 24 has an inner mounting edge and an outer mounting edge. The inner mounting edge of the deflector 24 is assembled to the sealing ring assembly 23 using mounting bolts 25. For example... Figure 3 As shown, the outer mounting edge of the guide plate 24 is a double-protrusion lace structure 241. This double-protrusion lace structure 241 includes a first protrusion 2411 and a second protrusion 2412 arranged axially back and forth. There is a certain distance between the first protrusion 2411 and the second protrusion 2412. There is a notch 2413 between two circumferentially adjacent first protrusions 2411 and / or second protrusions 2412, thus forming a lace structure. The height (i.e., outer diameter) of the first protrusion 2411 and the second protrusion 2412 is different. The height of the first protrusion 2411 closer to the turbine disk 21 is greater than the height of the second protrusion 2412 farther from the turbine disk 21. This is to prevent the first protrusion 2411 from entering the circumferential notch of the plug lace structure 231 of the sealing ring assembly 23 due to excessive axial rearward push during assembly caused by human error.

[0067] Combination Figure 3 and Figure 4 As shown, the outer diameter end of the sealing ring assembly 23 is provided with a radially extending plug lace structure 231, and the plug lace structure 231 is also provided with a notch in the circumferential direction, thus forming a lace structure.

[0068] During assembly, the guide plate 24 is rotated circumferentially so that the notch in the plug lace structure 231 of the sealing ring assembly 23 corresponds to the second boss 2412 in the double-bore lace structure 241 of the guide plate 24. The height of the second boss 2412 is less than the depth of the notch in the plug lace structure 231, so that the second boss 2412 can be directly inserted into the plug lace structure 231 of the sealing ring assembly 23. At the same time, the height of the first boss 2411 is greater than the depth of the notch in the plug lace structure 231. After the second boss 2412 passes through the notch, the plug lace structure 231 is limited by the first boss 2411. Then, the guide plate 24 is rotated so that the double-bore lace structure 241 and the plug lace structure 231 are in the same circumferential position to prevent the guide plate 24 from moving back and forth. The gap formed by the lace notch after assembly can serve as a venting groove, as a pressure equalization channel for the chamber formed between the guide plate 24 and the sealing ring assembly 23.

[0069] like Figure 5 As shown, the outer diameter end of the sealing ring assembly 23 is configured as an end structure 232 with an approximately I-shaped cross-section. Grooves are formed on both sides of the end structure 232, which respectively form an air passage bite seal with the rear baffle 22 and the inner flow channel plate 29. An oil passage hole 233 is provided on the lower side of the end structure 232 of the sealing ring assembly 23. Leaked lubricating oil flows out through the oil passage hole 233. The top position of the end structure 232 is conducive to maintaining the aerodynamic performance of the main flow channel.

[0070] like Figure 6As shown, the inner diameter end of the sealing ring assembly 23 is equipped with an oil receiving groove 234. The axial length of the oil receiving groove 234 is determined according to the assembly requirements of the mounting bolts 25 and the farthest position S1 and the closest position S2 of the oil throwing path, so as to prevent oil droplets from exceeding the range of the oil receiving groove 234 after being thrown out by the centrifugal rotation of the toothed ring 27. The oil receiving groove 234 is provided with an oil leakage hole 235, which is used to allow leaked lubricating oil to flow out along the oil passage of the rear cavity of the disc.

[0071] like Figure 7 and Figure 8 As shown, the inner diameter end of the grate ring 27 is provided with an axially inclined oil receiving ring 271. The oil receiving ring 271 is a complete ring structure, and a stop 272 pointing towards the axis is located at the right end of the oil receiving ring 271. The right end face of the stop 272 at least partially overlaps with the left end face of the contact sealing assembly 28 to form an axial overlap, so as to ensure that oil droplets leaking from the contact sealing assembly 28 can flow smoothly into the space between the grate ring 27 and the turbine shaft 26. The surface of the main body of the grate ring 27 facing the turbine shaft 26 is provided with oil slinger grooves 273, and multiple oil slinger grooves 273 are evenly distributed circumferentially. In a preferred embodiment of this application, the cross-section of the oil slinger grooves 273 adopts a large aspect ratio design—that is, a small axial depth and a large circumferential width (e.g., a width-to-depth ratio greater than 10), which ensures the oil slingering area while reducing gas leakage.

[0072] The turbine disk 21 has a vent hole 211 on its support arm. Cooling air is introduced through the center of the turbine disk 21, enters the rear cavity of the disk through the vent hole 211 on the support arm, and then flows upward along the bent channel formed between the turbine disk 21 and the guide plate 24. It then flows through the bite structure formed by the rear baffle 22 and the sealing ring assembly 23 to the main channel and is discharged.

[0073] During the transition state, a small amount of lubricating oil in the oil chamber flows out through the gap between the contact sealing assembly 28 and the rotor, dripping onto the oil receiving ring 271 between the turbine shaft 26 and the grate ring 27. Under the action of centrifugal force, it flows along the inclined oil receiving ring 271 into the oil slinger 273, and then into the oil receiving groove 234 of the sealing ring assembly 23. It flows through the oil leakage hole 235 into the chamber pressure equalization channel between the guide plate 24 and the sealing ring assembly 23, and then flows into the front gap of the inner flow channel plate 29 through the oil passage hole 233 at the outer diameter end of the sealing ring assembly 23, and finally enters the main flow channel.

[0074] The oil-gas separation engine turbine disk rear cooling structure provided in this application can effectively separate the exhaust flow path and lubricating oil flow path of the turbine disk rear cavity of aero-engines / gas turbines, preventing leaked lubricating oil from directly contacting the high-temperature components of the turbine rotor. At the same time, the separation structure is designed as a flexible conformal flow guide structure, which reduces the cross-sectional area of ​​the exhaust channel behind the disk, allowing the cooling airflow to accelerate and uniformly cool the surface of the hot-end rotor components—such as the turbine disk and baffles. This effectively reduces the temperature rise of the airflow in the rear cavity along the flow process, improves the rear cooling effect, and enhances engine safety.

[0075] 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 aftercooling structure for oil-gas separation, characterized in that, The rear-disc cooling structure includes: a turbine disk, a rear baffle, a sealing ring assembly, a guide plate, mounting bolts, a turbine shaft, a grate ring, and a contact sealing assembly; The turbine disk is fixedly connected to the turbine shaft and the grate ring to form a rotor; The guide plate and sealing ring assembly are assembled together by mounting bolts to form a stator. The guide plate is a flexible thin-walled structure, which enables the guide plate to have unloading and coordinated deformation capabilities. The flexible thin-walled structure profile and dimensions of the guide plate are determined according to the arc-shaped rotor wall shape formed by the turbine disk and the rear baffle. The spacing between the guide plate and the rotor is determined according to the deformation of the rotor-stator under the ultimate state. The turbine disk, the rear baffle, and the sealing ring assembly form a rear disk cavity. The guide plate is located in the rear disk cavity and between the turbine disk and the sealing ring assembly, thereby separating the cooling gas flowing into the turbine disk center from the lubricating oil leaking into the rear disk cavity through the contact sealing assembly, forming separate cooling gas acceleration channels and lubricating oil flow channels.

2. The engine turbine disk aftercooling structure with oil-gas separation as described in claim 1, characterized in that, The guide plate has an inner mounting edge and an outer mounting edge. The inner mounting edge is assembled to the front side of the sealing ring assembly by mounting bolts. The outer mounting edge is a double-protrusion lace structure. The double-protrusion lace structure includes a first protrusion and a second protrusion arranged axially front and rear. The first protrusion and the second protrusion both have corresponding notches in the circumferential direction to form a lace structure.

3. The engine turbine disk aftercooling structure with oil-gas separation as described in claim 2, characterized in that, The first boss is closer to the turbine disk than the second boss, and the height of the first boss, which is closer to the turbine disk, is greater than the height of the second boss, which is farther away from the turbine disk.

4. The engine turbine disk aftercooling structure with oil-gas separation as described in claim 2 or 3, characterized in that, The outer diameter end of the sealing ring assembly is provided with a radially extending plug lace structure, and the plug lace structure has a notch in the circumferential direction to form a lace structure; The plug lace structure at the outer diameter end of the sealing ring assembly is inserted into the double boss lace structure on the outer mounting edge of the guide plate. The notch in the plug lace structure and the notch in the double boss lace structure are connected to form a ventilation groove, which serves as a pressure equalization channel between the guide plate and the sealing ring assembly.

5. The engine turbine disk aftercooling structure with oil-gas separation as described in claim 4, characterized in that, The outer diameter end of the sealing ring assembly is configured as an I-shaped end structure, and the two sides of the end structure form grooves to form an air passage bite seal with the rear baffle and the inner flow channel plate respectively; The sealing ring assembly has an oil passage hole on the lower side of its end structure, through which leaked lubricating oil flows out from the lubricating oil flow channel.

6. The engine turbine disk aftercooling structure with oil-gas separation as described in claim 5, characterized in that, The inner diameter end of the sealing ring assembly is provided with an oil receiving groove. The axial length of the oil receiving groove is determined according to the assembly requirements of the mounting bolts and the farthest and closest positions of the oil throwing path of the grate ring. The oil receiving groove is provided with an oil leakage hole, which is used to allow the lubricating oil leaking through the contact sealing assembly to enter the lubricating oil flow channel of the rear cavity of the disc along the oil leakage hole.

7. The engine turbine disk aftercooling structure with oil-gas separation as described in claim 6, characterized in that, The inner diameter end of the toothed ring is provided with an axially inclined oil receiving ring with a solid ring structure. The end of the oil receiving ring has a notch pointing in the axial direction. The end face of the notch at least partially overlaps with the end face of the contact sealing assembly. The main body of the toothed ring has an oil slinger groove on the surface facing the turbine shaft. The lubricating oil leaking from the contact sealing assembly, collected by the oil receiving ring, flows along the oil slinger groove towards the oil receiving groove under the centrifugal force of the rotor.

8. The engine turbine disk after-cooling structure with oil-gas separation as described in claim 7, characterized in that, There are multiple oil-slinging grooves, which are evenly distributed in the circumferential direction.

9. The engine turbine disk after-cooling structure with oil-gas separation as described in claim 7, characterized in that, The cross-section of the oil slinger is designed with a large aspect ratio, which means that the circumferential width is greater than the axial depth.

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