An online balancing structure and method for rotor components of an aircraft engine core

Abstract

The present application belongs to the technical field of rotor component balancing of an aircraft engine core machine, and specifically relates to an online balancing structure and method for rotor components of an aircraft engine core machine, wherein the online balancing structure for rotor components of the core machine comprises: a rotor component, which is a combination of a high-pressure compressor and a high-pressure turbine; a stator component, which is assembled with the rotor component, wherein the casing is a split casing; a semi-annular simulated casing, which replaces half of the split casing for assembly and has a high-pressure compressor balance adjustment window thereon; a front process support casing, which is butt-jointed with the front end of the stator component, and whose side wall has a front annular process support edge; a rear process support casing, which is butt-jointed with the rear end of the stator component, and has a rear annular process support edge and a high-pressure turbine rear end annular support edge thereon, and whose side wall has a high-pressure turbine balance adjustment window; a high-pressure turbine rear end support bearing, which is sleeved on the high-pressure turbine rear end annular support edge and supported between the high-pressure turbine rear end annular support edge and the high-pressure turbine rear end.

Description

Technical Field

[0001] The present application belongs to the technical field of rotor component balancing of an aircraft engine core machine, and specifically relates to an online balancing structure and method for rotor components of an aircraft engine core machine. Background Art

[0002] The rotor components of the core of an aircraft engine mainly include the high-pressure compressor and the high-pressure turbine, which need to be balanced before installation. Currently, the balancing of the rotor components of the core of an aircraft engine is mostly carried out in the following ways:

[0003] Balance the high-pressure compressor and high-pressure turbine separately;

[0004] Balance the combination of high-pressure compressor and high-pressure turbine.

[0005] After the rotor components of the aircraft engine core are balanced, the high-pressure compressor and high-pressure turbine assembly must be disassembled before they can be assembled with the stator components of the aircraft engine core. During assembly, repeated assembly errors will inevitably be introduced, making it difficult to ensure the balance after assembly with the stator components. Moreover, the unbalance amount is difficult to measure and adjust using existing technology when the stator components are assembled. Only after the aircraft engine is installed and the bench test is carried out, can it be measured and adjusted using the machine's balancing method. It is easy for the rotor components to vibrate beyond the limit, and multiple bench tests are required to determine the unbalance amount of the rotor components. The aircraft engine needs to be disassembled multiple times to complete the adjustment of the rotor component balance. The process is cumbersome, time-consuming and laborious.

[0006] In addition, currently, when balancing the combination of the high-pressure compressor and the high-pressure turbine, the balancing sleeve is sleeved on the front journal of the high-pressure compressor, connected to the balancing machine, and the combination of the high-pressure compressor and the high-pressure turbine is driven. The front fulcrum of the rotor component is supported on the balancing machine through the balancing sleeve, such as Figure 1 As shown, in reality, the front fulcrum of the rotor component is supported on the stator component by a third fulcrum bearing sleeved on the front journal of the high-pressure compressor. When balancing the combination of the high-pressure compressor and the high-pressure turbine, the front fulcrum deviates from the actual position of the front fulcrum. The existence of this deviation makes it difficult to ensure the balance of the rotor component and the stator component of the aircraft engine core after assembly.

[0007] This application is proposed in view of the above-mentioned technical defects.

[0008] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the invention

[0009] The purpose of the present application is to provide an online balancing structure and method for rotor components of an aircraft engine core machine, so as to overcome or alleviate at least one of the known technical defects.

[0010] The technical solution of this application is:

[0011] On the one hand, an online balancing structure of a rotor component of an aircraft engine core is provided, comprising:

[0012] The rotor component is a combination of a high-pressure compressor and a high-pressure turbine;

[0013] The stator component is assembled with the rotor component, wherein the casing is a split casing;

[0014] A semi-circular simulated casing is installed to replace the half of the split casing, and has a high-pressure compressor balance adjustment window on it;

[0015] A front process support casing is butted against the front end of the stator component, and a side wall thereof has a front ring process support edge;

[0016] A rear process support casing is butted with the rear end of the stator component, and is provided with a rear annular process support edge and a rear annular support edge of the high-pressure turbine, and a high-pressure turbine balance adjustment window on the side wall;

[0017] The high-pressure turbine rear end support bearing is sleeved on the high-pressure turbine rear end annular support edge and supported between the high-pressure turbine rear end annular support edge and the high-pressure turbine rear end.

[0018] According to at least one embodiment of the present application, in the online balancing structure of the rotor component of the above-mentioned aircraft engine core machine, the high-pressure compressor balance adjustment window is located at the position corresponding to the 4th to 9th stages of the high-pressure compressor.

[0019] According to at least one embodiment of the present application, in the online balancing structure of the rotor component of the above-mentioned aircraft engine core machine, the high-pressure turbine balance adjustment window is located at the corresponding position of the balance bolt and its balance block at the rear end of the high-pressure turbine.

[0020] According to at least one embodiment of the present application, the above-mentioned rotor component online balancing structure of the aircraft engine core machine further includes:

[0021] The drive shaft has one end extending into the front journal of the high-pressure compressor for connection;

[0022] Universal coupling, connected to the other end of the drive shaft.

[0023] On the other hand, a method for online balancing of a rotor component of an aircraft engine core is provided, comprising:

[0024] Balance the high-pressure compressor and high-pressure turbine separately;

[0025] Assembling any of the above-mentioned rotor component online balancing structures of the core machine of the aircraft engine;

[0026] Support the front ring process support edge and the rear ring process support edge on the balancing machine, connect the balancing machine to the universal coupling, drive the rotor component to rotate, and measure the unbalance amount of the rotor component;

[0027] The imbalance amount of the high-pressure compressor is adjusted through the high-pressure turbine balance adjustment window, and the imbalance amount of the high-pressure turbine is adjusted through the high-pressure turbine balance adjustment window. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the existing balancing of the combination of a high-pressure compressor and a high-pressure turbine;

[0029] Figure 2 It is a schematic diagram of an online balancing structure of a rotor component of an aircraft engine core machine provided in an embodiment of the present application;

[0030] in:

[0031] 1-rotor component; 2-stator component; 3-semi-annular simulation casing; 4-front process support casing; 5-rear process support casing; 6-high-pressure turbine rear end support bearing; 7-drive shaft; 8-universal coupling.

[0032] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0033] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0034] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, 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, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0035] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the 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, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0036] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

[0037] On the one hand, an online balancing structure of a rotor component of an aircraft engine core is provided, comprising:

[0038] The rotor component 1 is a combination of a high-pressure compressor and a high-pressure turbine;

[0039] The stator component 2 is assembled with the rotor component 1, wherein the casing is a split casing;

[0040] A semi-annular simulated casing 3 is installed to replace the half of the split casing and has a high-pressure compressor balance adjustment window;

[0041] The front process support casing 4 is butted against the front end of the stator component 2, and its side wall has a front ring process support edge;

[0042] The rear process support casing 5 is butted with the rear end of the stator component 2, and has a rear annular process support edge and a high-pressure turbine rear end annular support edge, and a high-pressure turbine balance adjustment window on the side wall;

[0043] The high-pressure turbine rear end support bearing 6 is sleeved on the high-pressure turbine rear end annular support edge and supported between the high-pressure turbine rear end annular support edge and the high-pressure turbine rear end.

[0044] The rotor components of the aircraft engine core machine are balanced by the online balancing structure of the rotor components of the aircraft engine core machine disclosed in the above embodiment, and the following steps can be referred to:

[0045] Balance the high-pressure compressor and high-pressure turbine separately;

[0046] Assembling the above-mentioned rotor component online balancing structure of the aircraft engine core machine;

[0047] The front ring process support edge and the rear ring process support edge are supported on the balancing machine, specifically, they can be supported on the balancing table by a fulcrum structure;

[0048] driving the rotor component 1 to rotate and measuring the unbalance amount of the rotor component 1;

[0049] The imbalance of the high-pressure compressor is adjusted through the high-pressure turbine balance adjustment window, and the imbalance of the high-pressure turbine is adjusted through the high-pressure turbine balance adjustment window to complete the balancing of the rotor components of the aircraft engine core.

[0050] After the online balancing structure of the rotor components of the aircraft engine core machine disclosed in the above embodiment is used to balance the rotor components of the aircraft engine core machine, the front process support casing 4, the rear process support casing 5, and the high-pressure turbine rear end support bearing 6 can be removed, and the semi-annular simulation casing 3 can be removed and replaced with a semi-open casing to replace the semi-open casing, so as to realize the assembly of the rotor components and stator components of the aircraft engine core machine. During this process, it is not necessary to re-disassemble the combination of the high-pressure compressor and the high-pressure turbine. After assembly with the stator component, no repeated assembly error will be introduced, and the balance of the rotor components and stator components of the aircraft engine core machine after assembly can be ensured. The balancing of the rotor components of the aircraft engine core machine is achieved online by adjusting the unbalanced amount of the high-pressure compressor through the high-pressure turbine balance adjustment window, and adjusting the unbalanced amount of the high-pressure turbine through the high-pressure turbine balance adjustment window. After assembly with the stator component, it can be directly installed. The process is simple, which can greatly improve the installation efficiency and greatly reduce the possibility of excessive vibration of the rotor components during the aircraft engine bench test.

[0051] As for the online balancing structure of the rotor component of the aircraft engine core machine disclosed in the above-mentioned embodiment, technicians in the field can understand that the balancing of the rotor component of the aircraft engine core machine is carried out when it is assembled with the stator component, and the front fulcrum position is restored to the actual situation, which can effectively ensure the balance of the rotor component of the aircraft engine core machine and the stator component after assembly.

[0052] In some optional embodiments, in the online balancing structure of the rotor components of the above-mentioned aircraft engine core machine, the high-pressure compressor balance adjustment window is located at the position corresponding to the 4th to 9th stages of the high-pressure compressor. When balancing the rotor components of the aircraft engine core machine, the rotor blades of the 4th to 9th stages of the high-pressure compressor can be conveniently removed through the high-pressure compressor balance adjustment window, and the balance block set at the root of the rotor blade can be adjusted.

[0053] In some optional embodiments, in the online balancing structure of the rotor components of the above-mentioned aircraft engine core machine, the high-pressure turbine balancing adjustment window is located at the corresponding position of the high-pressure turbine rear end balancing bolt and its balancing block. When the rotor components of the aircraft engine core machine are balanced, the high-pressure turbine rear end balancing bolt and its balancing block can be conveniently replaced through the high-pressure turbine balancing adjustment window.

[0054] In some optional embodiments, the above-mentioned rotor component online balancing structure of the aircraft engine core machine further includes:

[0055] One end of the drive shaft 7 is inserted into the front journal of the high-pressure compressor for connection, and a stop pin may be provided on the drive shaft 7 to be inserted into the anti-twist groove in the front journal of the high-pressure compressor to achieve connection;

[0056] The universal coupling 8 is connected to the other end of the drive shaft 7. When balancing the rotor component of the aircraft engine core, it can be connected to a balancing machine and connected to a motor to drive the rotor component 1 to rotate, thereby measuring the imbalance of the rotor component 1. The specific means for measuring the imbalance of the rotor component 1 can be designed and selected by relevant technical personnel according to specific actual conditions when applying this application.

[0057] On the other hand, a method for online balancing of a rotor component of an aircraft engine core is provided, comprising:

[0058] Balance the high-pressure compressor and high-pressure turbine separately;

[0059] Assembling any of the above-mentioned rotor component online balancing structures of the core machine of the aircraft engine;

[0060] Support the front ring process support edge and the rear ring process support edge on a balancing machine, connect the universal coupling 8 with the balancing machine, drive the rotor component 1 to rotate, and measure the unbalance amount of the rotor component 1;

[0061] The imbalance amount of the high-pressure compressor is adjusted through the high-pressure turbine balance adjustment window, and the imbalance amount of the high-pressure turbine is adjusted through the high-pressure turbine balance adjustment window.

[0062] The online balancing method for rotor components of an aircraft engine core machine disclosed in the above-mentioned embodiment is implemented based on the online balancing structure of rotor components of an aircraft engine core machine disclosed in the above-mentioned embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the online balancing structure of rotor components of an aircraft engine core machine. Its technical effects can also refer to the technical effects of the relevant parts of the online balancing structure of rotor components of an aircraft engine core machine, which will not be repeated here.

[0063] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0064] So far, the technical solution of the present 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 the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present 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 fall within the scope of protection of the present application.

Claims

1. An online balancing structure for rotor components of an aircraft engine core, characterized in that: include: The rotor component (1) is a combination of a high-pressure compressor and a high-pressure turbine; A stator component (2) is assembled with the rotor component (1), wherein the casing is a split casing; A semi-annular simulated casing (3) is installed to replace one half of the split casing and is provided with a high-pressure compressor balance adjustment window; A front process support casing (4) is butted against the front end of the stator component (2), and its side wall has a front ring process support edge; A rear process support casing (5) is butted against the rear end of the stator component (2), and is provided with a rear annular process support edge and a high-pressure turbine rear end annular support edge, and a side wall thereof is provided with a high-pressure turbine balance adjustment window; The high-pressure turbine rear end support bearing (6) is sleeved on the high-pressure turbine rear end annular support edge and supported between the high-pressure turbine rear end annular support edge and the high-pressure turbine rear end.

2. The online balancing structure of the rotor components of the aircraft engine core according to claim 1 is characterized in that: The high-pressure compressor balance adjustment window is located at positions corresponding to stages 4 to 9 of the high-pressure compressor.

3. The online balancing structure of the rotor components of the aircraft engine core according to claim 1, characterized in that: The high-pressure turbine balance adjustment window is located at the corresponding position of the balance bolt and the balance block at the rear end of the high-pressure turbine.

4. The online balancing structure of the rotor components of the aircraft engine core according to claim 1, characterized in that: Also includes: A drive shaft (7), one end of which extends into the front journal of the high-pressure compressor for connection; A universal coupling (8) is connected to the other end of the drive shaft (7).

5. An online balancing method for rotor components of an aircraft engine core, characterized in that: include: Balance the high-pressure compressor and high-pressure turbine separately; Assembling an online balancing structure for rotor components of an aircraft engine core machine according to any one of claims 1 to 4; The front ring process support edge and the rear ring process support edge are supported on a balancing machine, the balancing machine is connected to a universal coupling (8), the rotor component (1) is driven to rotate, and the unbalance amount of the rotor component (1) is measured; The imbalance amount of the high-pressure compressor is adjusted through the high-pressure compressor balance adjustment window, and the imbalance amount of the high-pressure turbine is adjusted through the high-pressure turbine balance adjustment window.

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