Aero-engine rotor axial force balancing structure
By introducing a balanced bleed air hole and a grate sealing ring into the aero-engine rotor, the high risk and high cost associated with turbine disk adjustment have been solved, achieving low-cost and efficient axial force balance and improving the performance and reliability of the aero-engine.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC SHENYANG ENGINE RES INST
- Filing Date
- 2023-09-11
- Publication Date
- 2026-05-19
AI Technical Summary
Existing technologies for adjusting the axial load of aero engines involve high risks, high costs, and low verification efficiency in turbine disk adjustment. In particular, modifications to the turbine disk can easily lead to insufficient sealing and insufficient cooling, and the processing cost of high-temperature alloy materials is high.
A rotor axial force balancing structure for an aero-engine is designed. By setting balancing air bleed holes and grate sealing rings on the inner ring of the stator, static pressure gas is introduced into the rear disk cavity of the compression component to balance the axial force. The structure is supported by a load-bearing ring and a load-bearing support plate, reducing the need for modifications to the turbine disk.
This approach effectively balances axial loads while reducing modification costs and risks, improving the overall performance and reliability of aero engines and simplifying the verification process.
Smart Images
Figure CN117189690B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aero-engine rotor axial force balance design technology, specifically relating to an aero-engine rotor axial force balance structure. Background Technology
[0002] The axial load in an aero-engine consists of two parts: the axial force of the main flow path and the axial force of the air system. The axial force of the main flow path is generated by the difference in the flow velocity of the main flow path and the pressure on both sides of the rotor blades. The axial force of the air system is generated by the pressure inside the aero-engine acting on the rotor components such as the compression disk and turbine disk.
[0003] Modern turbofan engines are typically upgraded by continuously improving the performance of their components, gradually enhancing overall engine performance. Component improvements often require minimal structural modifications to improve engine performance while maintaining reliability as much as possible. However, these improvements often alter the axial load on the engine, affecting bearing life. Therefore, to ensure the benefits of component improvements, the axial load on the engine needs to be balanced.
[0004] Generally, the axial force in the main flow path of an aero-engine is determined by the aero-engine performance design. The adjustment of axial load is mainly achieved through the adjustment of the air system. Currently, this is mostly achieved by adjusting the turbine disk chamber pressure. This technical solution has the following drawbacks:
[0005] 1) The turbine is a hot-end component. Adjusting its air system can easily lead to problems such as insufficient turbine disk edge sealing, insufficient blade root cooling, and increased temperature of the support seal. These problems are unpredictable and pose a high technical risk.
[0006] 2) Turbine components are usually made of high-temperature alloy materials, which are expensive. The cost of processing and producing new parts due to changes in structural dimensions is high, and a lot of resources need to be invested to re-verify the air system, which is costly and has low verification efficiency.
[0007] This application is made in view of the aforementioned technical deficiencies.
[0008] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention
[0009] The purpose of this application is to provide an axial force balancing structure for an aero-engine rotor to overcome or mitigate at least one of the known technical defects.
[0010] The technical solution of this application is:
[0011] An axial force balancing structure for an aero-engine rotor includes:
[0012] The compression rotor assembly includes a rotor disk and multiple rotor blades connected to the outer edge of the rotor disk;
[0013] The stator component of the compression component is at the same level as the rotor component of the compression component and is located after the rotor component of the compression component. It includes an inner stator ring and multiple stator blades connected to the outer side of the inner stator ring. The inner stator ring has multiple circumferentially distributed balance air bleed holes on its sidewall. Each balance air bleed hole is located after the stator blade.
[0014] The grate sealing ring is installed inside the stator inner ring and seals the front end of the stator inner ring with the grate. Its front end has an inward annular connecting edge and an outward annular guiding edge. The inward annular connecting edge is connected to the rear side of the outer edge of the rotor disk, and the outward annular guiding edge extends to the annular gap between the lower edge plate of the rotor blade and the stator inner ring.
[0015] According to at least one embodiment of this application, in the above-mentioned aero-engine rotor axial force balancing structure, the stator inner ring is divided into front and rear sections, and the two sections are fitted with a stop joint.
[0016] Each stator blade is connected to the outer side of the inner ring of the front stator;
[0017] Each balancing air vent is located on the inner ring sidewall of the rear stator.
[0018] According to at least one embodiment of this application, in the above-described aero-engine rotor axial force balancing structure, the inner side of the stator inner ring front end corresponding to the part of the grate sealing ring is coated with a sealing coating.
[0019] According to at least one embodiment of this application, in the above-described aero-engine rotor axial force balancing structure, the edge of the inward annular connecting edge is bent forward and extends into the rear side of the outer edge of the rotor disk.
[0020] According to at least one embodiment of this application, in the above-described aero-engine rotor axial force balancing structure, the rear end of the stator inner ring has an inward annular folded edge.
[0021] The aero-engine rotor axial force balancing structure also includes:
[0022] The load-bearing ring has its front outer side supported on the inner side of the inward annular fold, and a stop fits between it and the inward annular fold.
[0023] Multiple load-bearing plates are connected circumferentially to the outer rear end of the load-bearing ring at the front edge of the root, abutting against the inward annular folded edge, and fitting with the stop between them and the load-bearing ring. Attached Figure Description
[0024] Figure 1 This is a schematic diagram of the axial force balancing structure of the aero-engine rotor provided in the embodiments of this application;
[0025] in:
[0026] 1-Compression component rotor assembly; 2-Rotor disc; 3-Rotor blade; 4-Compression component stator assembly; 5-Stator inner ring; 6-Stator blade; 7-Grate sealing ring; 8-Bearing ring; 9-Bearing support plate;
[0027] A-Balanced air vent;
[0028] B - Compression component rear disc cavity.
[0029] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation
[0030] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.
[0031] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.
[0032] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a 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; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.
[0033] The following is in conjunction with the appendix Figure 1 This application will be described in further detail.
[0034] An axial force balancing structure for an aero-engine rotor includes:
[0035] The compression component rotor component 1 includes a rotor disk 2 and a plurality of rotor blades 3 connected to the outer edge of the rotor disk 2;
[0036] The stator component 4 of the compression component is at the same level as the rotor component 1 of the compression component and is located after the rotor component 1 of the compression component. It includes a stator inner ring 5 and a plurality of stator blades 6 connected to the outside of the stator inner ring 5. The stator inner ring 5 has a plurality of circumferentially distributed balance air vents A on its sidewall. Each balance air vent A is located after the stator blades 6.
[0037] The grate sealing ring 7 is set inside the stator inner ring 5 and seals the front end of the stator inner ring 5 with the grate. Its front end has an inward annular connecting edge and an outward annular guiding edge. The inward annular connecting edge is connected to the rear side of the outer edge of the rotor disk 2, and the outward annular guiding edge extends to the annular gap between the lower edge plate of the rotor blade 3 and the stator inner ring 5.
[0038] Based on the axial force balancing structure of the aero-engine rotor disclosed in the above embodiments, when the aero-engine is working, the static pressure gas that mainly flows into the six roots of the stator blades in the compression component can be partially introduced into the rear disk cavity B of the compression component through each balancing air intake hole A, and then flow forward to the fulcrum sealing cavity. This can increase the cavity pressure in the rear disk cavity B of the compression component, increase the forward axial force of the rotor, and eliminate the influence of axial load brought about by the improved design of components in the aero-engine.
[0039] In the axial force balancing structure of the aero-engine rotor disclosed in the above embodiments, the grate sealing ring 7 is installed inside the stator inner ring 5, and the grate seal between it and the front end of the stator inner ring 5 can seal the static pressure gas entering the rear disc cavity B of the compression component, preventing this part of the static pressure gas from leaking out from there. In addition, the outward annular guide edge at the front end of the grate sealing ring 7 is designed to extend to the annular gap between the lower edge plate of the rotor blade 3 and the stator inner ring 5, which can guide the static pressure gas leaking from the sealing part to the main flow of the compression component, avoiding forward flow and seriously affecting the overall performance of the aero-engine.
[0040] In the axial force balancing structure of the aero-engine rotor disclosed in the above embodiments, the design is to bleed air through the balancing air bleed hole A at the rear end of the inner ring 5 of the stator component 4 in the compression component, thereby eliminating the influence of axial load caused by the improved design of the aero-engine components. The structural modification is small, easy to carry out without processing, low modification cost, and can be quickly tested and verified. Moreover, it is a cold-end component, so the modification risk is low.
[0041] Regarding the axial force balancing structure of the aero-engine rotor disclosed in the above embodiments, those skilled in the art will understand that the compression component can be a low-pressure compressor or a high-pressure compressor. The rotor component 1 and the stator component 4 of the compression component are at the same level as the compression component. As for which level, it can be selected by relevant technical personnel according to the actual situation, so as to open a certain number and size of balancing air bleed holes A at the rear end of the inner ring 5 of the stator for air bleed, which can effectively eliminate the influence of axial load brought about by the component improvement design in the aero-engine.
[0042] In some optional embodiments, in the above-described aero-engine rotor axial force balancing structure, the stator inner ring 5 is divided into front and rear sections, with a stop fit between the two sections.
[0043] Each stator blade 6 is connected to the outer side of the inner ring of the front stator;
[0044] Each balancing air intake hole A is located on the inner ring sidewall of the rear stator.
[0045] In some optional embodiments, in the above-described aero-engine rotor axial force balancing structure, the inner side of the front end of the stator inner ring 5, corresponding to the part of the grate sealing ring 7, is coated with a sealing coating.
[0046] In some optional embodiments, in the above-described axial force balancing structure for the aero-engine rotor, the edge of the inward annular connecting edge is bent forward and extends into the rear side of the outer edge of the rotor disk 2, where a stop is fitted.
[0047] In some optional embodiments, in the above-described aero-engine rotor axial force balancing structure, the rear end of the stator inner ring 5 has an inward annular folded edge.
[0048] The aero-engine rotor axial force balancing structure also includes:
[0049] The load-bearing ring 8 has its front outer side supported on the inner side of the inward annular fold, and is fitted with a stop between it and the inward annular fold.
[0050] Multiple load-bearing plates 9 are connected circumferentially to the outer rear end of the load-bearing ring 8 at their root front edge, abutting against the inward annular folded edge, and fitting with the load-bearing ring 8 at a stop joint.
[0051] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.
[0052] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.
Claims
1. An axial force balancing structure for an aero-engine rotor, characterized in that, include: The compression component rotor component (1) includes a rotor disk (2) and a plurality of rotor blades (3) connected to the outer edge of the rotor disk (2); The stator component (4) of the compression component is at the same level as the rotor component (1) of the compression component and is located after the rotor component (1) of the compression component. It includes a stator inner ring (5) and a plurality of stator blades (6) connected to the outside of the stator inner ring (5). The sidewall of the stator inner ring (5) has a plurality of circumferentially distributed balance air vents (A); each balance air vent (A) is located after the stator blades (6). A toothed sealing ring (7) is provided inside the stator inner ring (5) and is sealed with teeth between the stator inner ring (5) and the front end of the stator inner ring (5). Its front end has an inward annular connecting edge and an outward annular guiding edge. The inward annular connecting edge is connected to the rear side of the outer edge of the rotor disk (2), and the outward annular guiding edge extends to the annular gap between the lower edge plate of the rotor blade (3) and the stator inner ring (5).
2. The aero-engine rotor axial force balancing structure according to claim 1, characterized in that, The inner ring (5) of the stator is divided into two sections, front and back, with a stop fitting between the two sections; Each stator blade (6) is connected to the outer side of the inner ring of the front stator; Each balancing air vent (A) is located on the inner ring sidewall of the rear stator.
3. The aero-engine rotor axial force balancing structure according to claim 1, characterized in that, The inner front end of the stator inner ring (5) is coated with a sealing coating corresponding to the part of the grate sealing ring (7).
4. The aero-engine rotor axial force balancing structure according to claim 1, characterized in that, The inner annular connecting edge bends forward and extends into the rear side of the outer edge of the rotor disk (2).
5. The aero-engine rotor axial force balancing structure according to claim 1, characterized in that, The rear end of the inner ring (5) of the stator has an inwardly oriented annular fold; The aero-engine rotor axial force balancing structure also includes: The load-bearing ring (8) has its front outer side supported on the inner side of the inward annular folded edge, and is fitted with a stop between it and the inward annular folded edge. Multiple load-bearing plates (9) are connected circumferentially to the outer side of the rear end of the load-bearing ring (8) at the front edge of the root, abutting against the inward annular folded edge, and fitting with the stop between the load-bearing ring (8).