A sealing structure for turbine rotor interstage seal and lubricating oil chamber seal

Abstract

The present invention belongs to the field of engines, and specifically relates to a sealing structure for sealing between stages of a turbine rotor and a lubricating oil chamber. It comprises a turbine disc, turbine blades, a turbine shaft, a runway ring, a sealing ring, a turbine disc chamber, and a lubricating oil chamber; a turbine disc is provided on the turbine shaft, and the turbine disc is connected to the turbine blades; an air inlet groove is provided between the turbine disc and the turbine shaft, and a first air vent is provided on the turbine disc in the air inlet groove, and the air vent is connected to the runway ring; a second air vent is provided on the runway ring, which is connected to the sealing ring, and a third air vent is provided on the runway ring, which is connected to the turbine disc chamber; the sealing ring is connected to the turbine disc chamber and the lubricating oil chamber, respectively. The present invention can ensure that the gas pressure required for sealing the turbine disc chamber is higher than the gas pressure for sealing the lubricating oil chamber.

Description

Technical Field

[0001] The invention belongs to the field of engines, and in particular relates to a sealing structure for a turbine rotor interstage seal and a lubricating oil cavity seal. Background Art

[0002] The turbine rotor is a key component of an aircraft engine, primarily consisting of a turbine disc, turbine blades, and a turbine shaft. Its function is to convert the kinetic energy of high-temperature combustion gases into mechanical energy. An axial gap inevitably exists between the rotor and stator between the turbine stages of an aircraft engine. If combustion gases from the main flow path pass through this gap and enter the turbine disc cavity on the side of the turbine rotor disc, the turbine disc temperature will rise sharply, seriously affecting its operational safety. Therefore, it is necessary to prevent high-temperature combustion gases from entering the turbine disc cavity.

[0003] In view of this, the present invention is proposed. Summary of the Invention

[0004] The present invention uses high-pressure gas to seal the axial gap between the rotor and stator, preventing high-temperature combustion gases from entering the turbine disc cavity. Furthermore, since the engine also contains a lubricating oil chamber, gas sealing is also required to prevent oil leakage. However, the gas pressure required to seal the interstage gap is higher than that required to seal the lubricating oil chamber.

[0005] In order to simultaneously seal the turbine disc cavity and the lubricating oil cavity, the present invention proposes a sealing structure for the turbine rotor interstage seal and the lubricating oil cavity seal. The present invention can ensure that the gas pressure required for sealing the turbine disc cavity is higher than the gas pressure for sealing the lubricating oil cavity.

[0006] The present invention comprises the following technical solutions:

[0007] The present invention provides a sealing structure for sealing between stages of a turbine rotor and sealing a lubricating oil cavity, comprising a turbine disc, turbine blades, a turbine shaft, a runway ring, a sealing ring, a turbine disc cavity and a lubricating oil cavity;

[0008] A turbine disc is provided on the turbine shaft, and the turbine disc is connected to the turbine blades;

[0009] An air intake groove is provided between the turbine disc and the turbine shaft, a first air vent is provided on the turbine disc in the air intake groove, and the air vent is communicated with the runway ring;

[0010] The raceway ring is provided with a second vent hole communicating with the sealing ring, and the raceway ring is provided with a third vent hole communicating with the turbine disc cavity;

[0011] The sealing ring is communicated with the turbine disc cavity and the lubricating oil cavity respectively.

[0012] Further, the runway ring is arranged between the turbine disc cavity and the lubricating oil cavity, and / or the sealing ring is arranged between the turbine disc cavity and the lubricating oil cavity.

[0013] Furthermore, the runway ring is arranged around the turbine disc.

[0014] Furthermore, the outer surface of the runway ring is cylindrical.

[0015] Further, the second ventilation holes are arranged in the radial direction of the runway ring, and the third ventilation holes are arranged in the axial direction of the runway ring.

[0016] Furthermore, the second ventilation holes are evenly arranged around the runway ring, and the third ventilation holes are evenly arranged around the runway ring.

[0017] Furthermore, the sealing ring is arranged around the outside of the runway ring, the sealing ring is communicated with the turbine disc cavity through a first gap between the sealing ring and the runway ring, and the sealing ring is communicated with the lubricating oil cavity through a second gap between the sealing ring and the runway ring.

[0018] Furthermore, the sealing ring includes a graphite sealing retainer, a front graphite sealing ring and a rear graphite sealing ring, the front graphite sealing ring and the rear graphite sealing ring are arranged at intervals, and the front graphite sealing ring and the rear graphite sealing ring are connected to the graphite sealing retainer away from the outside of the turbine shaft.

[0019] Furthermore, the cross section of the graphite sealing retainer is U-shaped.

[0020] Furthermore, the first vent holes are evenly arranged around the turbine disk.

[0021] By adopting the above technical solution, the present invention has the following advantages:

[0022] 1. The present invention can ensure that the gas pressure required for sealing the turbine disc cavity is higher than the gas pressure required for sealing the lubricating oil cavity. On the basis of saving high-pressure gas, it also plays a role in sealing the turbine disc cavity and the lubricating oil cavity at the same time.

[0023] 2. The present invention can achieve precise control of gas pressure and flow at different sealed positions in the engine system, thereby preventing backflow of gas between engine turbine stages and reducing the amount of gas entering the lubricating oil chamber, thereby minimizing gas loss and lowering the workload of the lubricating oil chamber.

[0024] 3. The present invention has good sealing performance of the turbine disc cavity and the lubricating oil cavity. On the premise of ensuring the sealing of the turbine disc cavity, the high-pressure gas entering the lubricating oil cavity is reduced by 50%.

[0025] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following is a brief introduction to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0027] Figure 1 Schematic diagram of a sealing structure for a turbine rotor interstage seal and a lubricating oil chamber seal according to an embodiment of the present invention Figure 1 ;

[0028] Figure 2 Schematic diagram of a sealing structure for a turbine rotor interstage seal and a lubricating oil chamber seal according to an embodiment of the present invention Figure 2 ;

[0029] In the accompanying drawings: 10-turbine disc, 110-first air vent, 20-turbine blade, 30-turbine shaft, 40-runway ring, 410-second air vent, 420-third air vent, 50-sealing ring, 51-first gap, 52-second gap, 510-graphite sealing retainer, 520-front graphite sealing ring, 530-rear graphite sealing ring, 60-turbine disc cavity, 70-lubricating oil cavity, 80-stator bracket, 90-bearing, 100-bearing seat. DETAILED DESCRIPTION

[0030] The following description provides many different embodiments or examples for implementing different features of the present invention. The components and arrangements described in the following specific examples are only used to simplify the present invention and are only used as examples, not to limit the present invention.

[0031] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present invention, the meaning of "multiple" is multiple or more, unless otherwise clearly and specifically defined.

[0032] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical, electrical, or intercommunication connections; direct or indirect connections through an intermediary; and may encompass internal connectivity between multiple components or interactions between multiple components. Those skilled in the art will understand the specific meanings of these terms in the present invention based on specific circumstances.

[0033] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may also include the first and second features not being in direct contact but being in contact via another feature between them. Furthermore, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or diagonally above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or diagonally below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0035] This embodiment provides a sealing structure for sealing between turbine rotor stages and lubricating oil chamber 70, such as Figure 1 、 Figure 2 As shown, it includes a turbine disc 10, turbine blades 20, a turbine shaft 30, a runway ring 40, a sealing ring 50, a turbine disc cavity 60 and a lubricating oil cavity 70; the turbine disc 10 is arranged on the turbine shaft 30, and the turbine disc 10 is connected to the turbine blades 20; an air intake groove is provided between the turbine disc 10 and the turbine shaft 30, and a first air vent 110 is provided on the turbine disc 10 in the air intake groove, and the air vent is connected to the runway ring 40; a second air vent 410 connected to the sealing ring 50 is provided on the runway ring 40, and a third air vent 420 connected to the turbine disc cavity 60 is provided on the runway ring 40; the sealing ring 50 is connected to the turbine disc cavity 60 and the lubricating oil cavity 70 respectively.

[0036] Among them, Figure 1 As shown, the turbine disc cavity 60 is the gap between the turbine disc 10 and the stator support 80. The lubricating oil chamber 70 is located between the bearing 90 and the bearing seat 100. The lubricating oil chamber 70 is mainly used to pass lubricating oil to lubricate the bearing 90. The stator support 80 can be fixedly connected to the bearing seat 100. Both the stator support 80 and the bearing seat 100 are fixed structures that do not rotate.

[0037] Working principle: High-pressure gas enters from the air inlet groove, enters the runway ring 40 through the first air vent 110, enters the sealing ring 50 through the second air vent 410 on the runway ring 40, and enters the turbine disc cavity 60 through the third air vent 420 of the runway ring 40; the high-pressure gas entering the sealing ring 50 enters the turbine disc cavity 60 and the lubricating oil cavity 70 respectively; the high-pressure gas entering the turbine disc cavity 60 is greater than the high-pressure gas entering the lubricating oil cavity 70, ensuring that the high-pressure gas in the turbine disc cavity 60 is at a higher pressure than the high-pressure gas entering the lubricating oil cavity 70.

[0038] Furthermore, the raceway ring 40 is disposed between the turbine disc cavity 60 and the lubricating oil cavity 70, and / or the sealing ring 50 is disposed between the turbine disc cavity 60 and the lubricating oil cavity 70. This provides a more rational structure, ensuring that the gas pressure required for sealing the interstage gap is higher than the gas pressure required for sealing the lubricating oil cavity 70 while also ensuring device miniaturization.

[0039] Furthermore, the runway ring 40 is disposed around the turbine disk 10 .

[0040] Furthermore, the outer surface of the runway ring 40 is cylindrical, which is conducive to forming a gap with the sealing ring 50 and is more conducive to assembly and manufacturing.

[0041] Furthermore, the second vent holes 410 are provided in the radial direction of the raceway ring 40 , and the third vent holes 420 are provided in the axial direction of the raceway ring 40 . The radial direction should be understood as the radial direction of the turbine shaft 30 , and the axial direction should be understood as the axial direction of the turbine shaft 30 .

[0042] Furthermore, the second vent holes 410 are evenly arranged around the runway ring 40, thereby making the high-pressure gas entering the sealing ring 50 more uniform and avoiding the loss of high-pressure gas pressure; and / or the third vent holes 420 are evenly arranged around the runway ring 40, thereby making the high-pressure gas entering the turbine disc cavity 60 more uniform and avoiding the loss of high-pressure gas pressure.

[0043] Furthermore, the sealing ring 50 is arranged around the runway ring 40, and the sealing ring 50 is connected to the turbine disc cavity 60 through a first gap 51 between the sealing ring 50 and the runway ring 40, and the sealing ring 50 is connected to the lubricating oil cavity 70 through a second gap 52 between the sealing ring 50 and the runway ring 40.

[0044] Furthermore, the sealing ring 50 includes a graphite sealing retainer 510, a front graphite sealing ring 520, and a rear graphite sealing ring 530. The front graphite sealing ring 520 and the rear graphite sealing ring 530 are spaced apart. The front graphite sealing ring 520 and the rear graphite sealing ring 530 are connected to the graphite sealing retainer 510 on the outside of the turbine shaft 30. The graphite sealing retainer 510 seals the outside of the front graphite sealing ring 520 and the rear graphite sealing ring 530 (i.e., the outside surface away from the turbine shaft 30). Based on this, the sealing ring 50 has a simple structure and is easy to assemble. At the same time, the structure of the front graphite sealing ring 520 and the rear graphite sealing ring 530 can reduce the flow rate of high-pressure gas flowing through the first gap 51 and the second gap 52 on both sides when the pressure difference is the same. The graphite sealing retainer 510 may be fixedly connected to the stator support 80 and / or the bearing seat 100 , so that the formed first gap 51 and / or the second gap 52 are more stable, and the flow of the high-pressure gas is smoother.

[0045] Furthermore, the cross section of the graphite sealing retainer 510 is U-shaped, thereby achieving a better sealing effect on the outer sides of the front graphite sealing ring 520 and the rear graphite sealing ring 530 .

[0046] Furthermore, the first vent holes 110 are evenly arranged around the turbine disk 10. Based on this, the high-pressure gas entering the runway ring 40 is made more uniform, thereby avoiding pressure loss of the high-pressure gas.

[0047] Based on the design of the specific positions and structures of the sealing ring 50 and the runway ring 40, the structure of the entire device is made more compact and reasonable, which not only facilitates manufacturing but also has the advantage of miniaturization.

[0048] Furthermore, if Figure 2 As shown, the diameter of the first vent hole 110 is 1.5S to 2S, the diameter of the second vent hole 410 is 1.5S to 2S, the diameter of the third vent hole 420 is 0.5S to 1S, the first gap 51 is 0.01S to 0.1S, and the second gap 52 is 0.01S to 0.1S. Based on this, the pressure of the high-pressure gas in the turbine disc cavity 60 can be accurately controlled to be greater than the pressure of the high-pressure gas entering the lubricating oil cavity 70.

[0049] Wherein: S = 0.8mm ~ 2mm, in a specific structure, the value of S should be consistent.

[0050] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A sealing structure for turbine rotor interstage seal and lubricating oil chamber seal, characterized in that: It includes turbine disc, turbine blades, turbine shaft, runway ring, sealing ring, turbine disc cavity and lubricating oil cavity; A turbine disc is provided on the turbine shaft, and the turbine disc is connected to the turbine blades; An air intake groove is provided between the turbine disc and the turbine shaft, a first air vent is provided on the turbine disc in the air intake groove, and the air vent is communicated with the runway ring; The raceway ring is provided with a second vent hole communicating with the sealing ring, and the raceway ring is provided with a third vent hole communicating with the turbine disc cavity; The sealing ring is communicated with the turbine disc cavity and the lubricating oil cavity respectively; The sealing ring is arranged around the outside of the raceway ring, and the sealing ring is communicated with the turbine disc cavity through a first gap between the sealing ring and the raceway ring, and the sealing ring is communicated with the lubricating oil cavity through a second gap between the sealing ring and the raceway ring; The sealing ring comprises a graphite sealing holder, a front graphite sealing ring and a rear graphite sealing ring, the front graphite sealing ring and the rear graphite sealing ring are arranged at intervals, and the front graphite sealing ring and the rear graphite sealing ring are connected to the graphite sealing holder at an outer side away from the turbine shaft; High-pressure gas enters from the air inlet groove, enters the runway ring through the first air vent, enters the sealing ring through the second air vent on the runway ring, and enters the turbine disc cavity through the third air vent of the runway ring; the high-pressure gas entering the sealing ring enters the turbine disc cavity through the first gap and enters the lubricating oil cavity through the second gap.

2. The sealing structure for turbine rotor interstage seal and lubricating oil chamber seal according to claim 1, characterized in that: The racetrack ring is arranged between the turbine disc cavity and the lubricating oil cavity, and / or the sealing ring is arranged between the turbine disc cavity and the lubricating oil cavity.

3. The sealing structure for turbine rotor interstage seal and lubricating oil chamber seal according to claim 1, characterized in that: The raceway ring is arranged around the turbine disc.

4. The sealing structure for turbine rotor interstage seal and lubricating oil chamber seal according to claim 3, characterized in that: The outer surface of the runway ring is cylindrical.

5. The sealing structure for turbine rotor interstage seal and lubricating oil chamber seal according to claim 4, characterized in that: The second ventilation holes are arranged in the radial direction of the racetrack ring, and the third ventilation holes are arranged in the axial direction of the racetrack ring.

6. The sealing structure for turbine rotor interstage seal and lubricating oil chamber seal according to claim 5, characterized in that: The second ventilation holes are evenly arranged around the runway ring, and the third ventilation holes are evenly arranged around the runway ring.

7. The sealing structure for turbine rotor interstage seal and lubricating oil chamber seal according to claim 1, characterized in that: The cross section of the graphite sealing retainer is U-shaped.

8. The sealing structure for turbine rotor interstage seal and lubricating oil chamber seal according to claim 1, characterized in that: The first vent holes are evenly and circumferentially arranged on the turbine disk.

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