A compressor rotor disc cavity air bleeding assembly and an aero-engine

Abstract

The application discloses a compressor rotor disc cavity air guide assembly and an aero-engine, and makes up the problems of many air guide device parts and large vibration of vortex reducers and the like, solves the problem of severe development of free vortex caused by air guide in the disc cavity, reduces pressure loss in the air guide process, and provides a more efficient, reliable and simple-structure air guide solution.The technical scheme is as follows: the compressor rotor disc cavity air guide assembly comprises a rotor disc and an air guide hole, the air guide hole is directly formed on the rotor disc and is a through hole penetrating through the rotor disc, high-pressure cooling gas in a main flow channel of the compressor is directly guided to a disc core of the rotor disc through the air guide hole on the rotor disc under the action of pressure difference, and the cooling gas can be used for cooling, sealing and heat insulation of bearings and high-temperature parts.Under the guidance of the cooling gas in the air guide hole, the air flow loss in the air guide process is reduced, the cooling efficiency is improved, and cooling, sealing and heat insulation are realized.

Description

Technical Field

[0001] This invention relates to aero-engine components, specifically to a compressor rotor disk cavity bleed air assembly and an aero-engine. Background Technology

[0002] In the field of aero-engines, with technological advancements, the pressure ratio of compressors has been continuously increasing, directly leading to an increase in the operating temperature of downstream compressor components. Effective cooling of these high-temperature components is one of the key challenges in modern aero-engine design. To reduce the temperature of these components, aero-engine design typically employs the method of extracting a portion of the high-pressure cooling gas between the compressor rotor stages.

[0003] Currently, a common method for interstage bleed gas in high-pressure compressors is to create bleed holes in the rotor drum and install vortex suppressors to guide the gas flow from the bleed holes to the rotor shaft, and then transmit the high-pressure gas to the high-temperature components. During the process of gas being introduced into the disk cavity from the main flow channel and flowing towards the shaft, the rotation of the disk cavity causes the airflow to move circumferentially, forming vortices, which can lead to significant airflow losses. To reduce these losses, vortex suppressors are typically equipped with vortex suppressor tubes to guide the gas flow, such as... Figure 1 As shown.

[0004] However, existing vortex suppressor designs have several problems. First, the large length-to-diameter ratio of the vortex suppressor presents challenges in design and manufacturing. Second, some vortex suppressors in bleed air assemblies are cantilevered, making them susceptible to vibration from high-pressure gas within the bleed air chamber, potentially leading to forced response or even flutter, which could damage the vortex suppressor. Furthermore, current bleed air assemblies often contain numerous parts and connecting joints, which not only places higher demands on the structure of the bleed air impeller but also increases the weight of the compressor.

[0005] In civil aircraft, the aero-engine is a crucial component. To improve passenger capacity, safety, and economy, civil aero-engines strive for performance indicators such as high thrust-to-weight ratio, high reliability, and low fuel consumption. Increasing the compressor pressure ratio, turbine inlet temperature, and reducing engine weight are effective means to improve these performance indicators. However, these improvements also introduce the problem of increased temperatures in high-temperature components. To reduce the temperature of components such as the turbine, the engine needs to draw high-pressure gas from the high-pressure compressor for cooling. Existing rotor bleed air assemblies suffer from problems such as complexity, large weight, numerous parts, difficulty in assembly and disassembly, and significant airflow losses during the bleed air process. Summary of the Invention

[0006] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0007] The purpose of this invention is to solve the above-mentioned problems and provide a compressor rotor disk cavity bleed air assembly and aero-engine, which makes up for the problems of many parts and large vibration of bleed air devices such as vortex reducers, effectively solves the problem of severe free vortex development caused by bleed air in the disk cavity, reduces pressure loss during the bleed air process, and provides a more efficient, reliable and simple bleed air solution.

[0008] The technical solution of this invention is as follows: This invention discloses a compressor rotor disk bleed air assembly, including a rotor disk and bleed air holes. The bleed air holes are formed directly on the rotor disk and are through holes penetrating the rotor disk. Under the action of pressure difference, the high-pressure cooling gas in the compressor's main flow channel is directly guided to the center of the rotor disk through the bleed air holes on the rotor disk. The cooling gas can be used for cooling, sealing, and heat insulation of bearings and high-temperature components. With the cooling gas guided by the bleed air holes, the airflow loss during the bleed air process is reduced, the cooling efficiency is improved, and cooling, sealing, and heat insulation are achieved.

[0009] According to one embodiment of the compressor rotor disk cavity bleed assembly of the present invention, the rotor disk is a hollow annular structure.

[0010] According to one embodiment of the compressor rotor disk cavity bleed assembly of the present invention, the rotor disk further includes a disk center, spokes, a drum, grating teeth, tenons, and rotor blades, wherein the disk center is located at the center of the rotor disk and bears the circumferential load of the disk; the spokes are located at the middle of the disk and bear the radial load of the disk; the drum connects the disk and the mounting edge and separates the inner and outer cavities of the rotor; the grating teeth and tenons are used to mount the rotor blades.

[0011] According to one embodiment of the compressor rotor disk cavity air intake assembly of the present invention, the disk core gradually thins from the inside out to the spokes.

[0012] According to one embodiment of the compressor rotor disk cavity air intake assembly of the present invention, the spokes adopt a cross-sectional shape design with equal strength.

[0013] According to one embodiment of the compressor rotor disk cavity air intake assembly of the present invention, one end of the air intake hole is connected to the junction of the drum and the tenon groove of the rotor disk, and the other end is connected to the disk center.

[0014] According to one embodiment of the compressor rotor disk cavity air intake assembly of the present invention, the starting end of the center line of the air intake hole is perpendicular to the junction of the drum and the tenon groove, and the ending end is perpendicular to the cylindrical surface at the center of the disk.

[0015] According to one embodiment of the compressor rotor disk cavity air intake assembly of the present invention, the air intake holes are evenly distributed circumferentially, and the cross-section of the air intake holes is circular to ensure that the airflow is uniformly drawn to the center of the disk.

[0016] According to one embodiment of the compressor rotor disk cavity air duct assembly of the present invention, the air duct is made by 3D printing or electrical discharge machining.

[0017] Furthermore, the present invention also discloses an aero engine including the compressor rotor disk bleed air assembly as described above.

[0018] Compared with the prior art, the present invention has the following beneficial effects: The technical innovation of the present invention lies in:

[0019] Several evenly distributed through holes, known as air ducts, are designed on the compressor rotor disc. These air ducts extend from the junction of the disc drum and the tenon groove to the disc center and can be manufactured by electrical discharge machining or 3D printing. This design allows cooling gas to flow directly from the compressor's main flow channel into the air ducts and then be guided towards the disc center by the air ducts.

[0020] Furthermore, the bleed air method of this invention features a simple structure, which does not increase the number of engine parts, nor does it increase the difficulty of assembly and disassembly. In addition, this design does not occupy additional structural space in the compressor, helping to maintain the engine's compactness and efficiency.

[0021] Based on the above-mentioned technical innovations, the beneficial effects of this invention are mainly reflected in the following aspects:

[0022] Simplified structure: The bleed air method adopted in this invention avoids the complex parts and connecting stops in traditional bleed air assemblies, thereby simplifying the design and manufacturing process of the engine.

[0023] Easy assembly: Due to the reduction in the number of parts, the air intake assembly of the present invention reduces the difficulty of assembly and disassembly, which helps to improve production efficiency and reduce maintenance costs.

[0024] Space utilization: The bleed air assembly of the present invention does not occupy additional structural space of the compressor, which helps to optimize the internal layout of the engine and may provide more space for other key components.

[0025] Improved cooling efficiency: High-pressure cooling gas is directly guided to the rotor center through bleed holes on the rotor disc, reducing airflow losses and improving cooling efficiency. This helps to cool bearings and high-temperature components more effectively, improving engine reliability and performance.

[0026] Multifunctionality: Guided by the bleed holes, the cooling gas can be used not only for cooling, but also for sealing and heat insulation, increasing the engine's multifunctionality.

[0027] In summary, this invention provides a compressor rotor disk cavity bleed air assembly that is simple in structure, easy to assemble, highly efficient in space utilization, highly efficient in cooling, and multifunctional, which helps to improve the overall performance of aero engines. Attached Figure Description

[0028] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0029] Figure 1 A schematic diagram of a tubular vortex reducer;

[0030] Figure 2 This is a schematic diagram of a compressor rotor disk cavity air bleed assembly according to a preferred embodiment of the present invention;

[0031] Figure 3 , Figure 4 yes Figure 2 A cross-sectional view of the rotor disk in the embodiment shown.

[0032] [Attached image labels]

[0033] 1—Rotor disc

[0034] 2—Air intake hole Detailed Implementation

[0035] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0036] In the description of this invention, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," and "the other end," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0037] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0038] Figure 2 The structure of one embodiment of the compressor rotor disk cavity bleed air assembly of the present invention is shown. Please refer to... Figure 2 The compressor rotor disk cavity air intake assembly in this embodiment includes a rotor disk 1 and an air intake hole 2.

[0039] The rotor disk 1, as the core component of this invention, functions as follows: under the action of pressure difference, the high-pressure gas in the compressor's main flow channel flows through the air vent 2 to the center of the rotor disk, achieving functions such as cooling, sealing, and heat insulation. The design of the air vent 2 reduces gas loss during the air venting process and improves cooling efficiency.

[0040] The rotor disk 1 is a hollow annular structure, comprising the following sub-components:

[0041] The center of the disc: Located in the center of the disc, it mainly bears the circumferential load of the disc. It is generally thicker and gradually thins from the inside to the outside, transitioning to the spokes.

[0042] Spokes: Located in the middle of the wheel, they are designed with a cross-sectional shape of equal strength and mainly bear the radial load of the wheel;

[0043] Drum: Connects the rotor disc and the mounting edge, and also separates the inner and outer cavities of the rotor;

[0044] Grate teeth: used to mount rotor blades;

[0045] Tenon and groove: used for mounting rotor blades.

[0046] The air vent 2 is an innovative feature of this invention. It is a through hole that penetrates the rotor disk 1 and has the following characteristics:

[0047] Location: One end is connected to the junction of the drum and the tenon of the rotor disc 1, and the other end is connected to the disc center.

[0048] Distribution: Evenly distributed along the circumference, with the cross-section of air intake hole 2 being circular to ensure that the airflow is evenly directed to the center of the disk.

[0049] Processing method: The air vent 2 can be processed by 3D printing or electrical discharge machining. Figure 3 The air vents in the design feature a uniform transition with arc segments, making them suitable for 3D machining. Figure 4The air vents in the middle have no transition section between the two sections, making them suitable for EDM machining.

[0050] Position and connection relationship between air vent 2 and rotor disk: Air vent 2 is formed directly on rotor disk 1, eliminating the need for additional connecting parts and simplifying the structure. Rotor disk 1 is connected to the mounting edge via a drum, and rotor blades are mounted via tenons. The starting end of the centerline of air vent 2 is perpendicular to the junction of the drum and tenon, and the ending end is perpendicular to the cylindrical surface at the center of the disk to reduce gas loss.

[0051] In addition, the total cross-sectional area of ​​the bleed air inlet 2 should meet the bleed air volume requirements proposed by the air system. If the bleed air wheel has bolt holes for connecting the rotor wheels, the strength of the rotor wheel connection should also be considered when designing the number and cross-sectional area of ​​the bleed air inlets to ensure the safety and reliability of the engine.

[0052] Furthermore, the present invention also discloses an aero-engine including an embodiment of the compressor rotor disk bleed air assembly as described above.

[0053] The prior description of this disclosure is provided to enable any person skilled in the art to make or use this disclosure. Various modifications to this disclosure will be apparent to those skilled in the art, and the general principles defined herein may be applied to other variations without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not intended to be limited to the examples and designs described herein, but should be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A compressor rotor disk cavity bleed air assembly, characterized in that, It includes a rotor disc and an air vent. The air vent is formed directly on the rotor disc and is a through hole that runs through the rotor disc. Under the action of pressure difference, the high-pressure cooling gas in the main flow channel of the compressor is directly guided to the center of the rotor disc through the air vent on the rotor disc. The cooling gas is used for cooling, sealing and heat insulation of bearings and high-temperature components. Under the guidance of the air vent, the airflow loss during the air venting process is reduced and the cooling efficiency is improved, achieving cooling, sealing and heat insulation.

2. The compressor rotor disk cavity bleed air assembly according to claim 1, characterized in that, The rotor disk has a hollow ring structure.

3. The compressor rotor disk cavity bleed air assembly according to claim 2, characterized in that, The rotor disk further includes a disk center, spokes, drum, grates, tenons, and rotor blades. The disk center is located in the central part of the rotor disk and bears the circumferential load of the disk. The spokes are located in the middle of the disk and bear the radial load of the disk. The drum connects the disk and the mounting edge and separates the inner and outer cavities of the rotor. The grates and tenons are used to install the rotor blades.

4. The compressor rotor disk cavity bleed air assembly according to claim 3, characterized in that, The center of the plate gradually thins outwards, transitioning to the spokes.

5. The compressor rotor disk cavity bleed air assembly according to claim 3, characterized in that, The spokes are designed with a cross-sectional shape of equal strength.

6. The compressor rotor disk cavity bleed air assembly according to claim 3, characterized in that, One end of the air vent is connected to the junction of the drum and the tenon of the rotor disc, and the other end is connected to the center of the disc.

7. The compressor rotor disk cavity bleed air assembly according to claim 6, characterized in that, The starting end of the air vent centerline is perpendicular to the junction of the drum and the tenon, and the ending end is perpendicular to the cylindrical surface at the center of the disc.

8. The compressor rotor disk cavity bleed air assembly according to claim 7, characterized in that, The air intake holes are evenly distributed circumferentially, and the cross-section of the air intake holes is circular to ensure that the airflow is evenly directed to the center of the disk.

9. The compressor rotor disk cavity bleed air assembly according to claim 8, characterized in that, The air vents are made using 3D printing or electrical discharge machining.

10. An aircraft engine, characterized in that, Includes the compressor rotor disk cavity air bleed assembly as described in any one of claims 1 to 9.

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