A casing containment test structure for aircraft engine rotor components

Abstract

The present application belongs to the technical field of aircraft engine rotor component casing containment test design, and specifically relates to an aircraft engine rotor component casing containment test structure, comprising: a casing; a rotor component, assembled in the casing; a support plate, connected to one end of the casing, and having a through hole thereon; a drive shaft, arranged through the through hole; a transfer shaft, arranged through the center of the rotor disc of the rotor component, with one end thereof facing the support plate connected to the end of the drive shaft facing the rotor component, and an outer wall thereof having an annular transfer edge; the annular transfer edge is connected to the rotor disc of the rotor component; a support cylinder, sleeved on the outer periphery of the drive shaft, with one end connected to the support plate and the other end sleeved on the outer periphery of the transfer shaft, with a gap left between the support cylinder and the transfer shaft; the support shaft, which is a hollow structure, sleeved on the other end of the transfer shaft, with a gap left between the support cylinder and the transfer shaft.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine rotor component casing containment test design, and specifically relates to an aircraft engine rotor component casing containment test structure. Background Art

[0002] The rotor components of an aircraft engine are located inside the casing, and mainly include the rotor disc and its rotor blades arranged circumferentially on the outer edge of the rotor disc. When the aircraft engine is working, the rotor components rotate at high speed, and there is a possibility that the rotor blades will break and fly off. In this case, the casing needs to have sufficient containment to prevent the broken rotor blades from flying out of the casing and causing damage to objects or personnel. For this purpose, a corresponding casing containment test is designed.

[0003] The containment test structure of the current aircraft engine rotor parts casing is used to conduct containment test on the casing, such as Figure 1 As shown, there are the following defects:

[0004] 1) After the rotor blades break and fly off, a large eccentric load will be generated on the rotor disc, and the center of the disc will rub against the supporting components, generating violent vibrations, causing damage to the rotor disc and the rotor blades to fall off, causing secondary damage to the casing;

[0005] 2) When a rotor blade breaks and flies off, only the impact load of the rotor disc on one side of the support can be measured, but the impact load of the rotor disc on the support points on both sides cannot be measured, and the eccentric load of the rotor disc when the rotor blade breaks and flies off cannot be accurately evaluated;

[0006] 3) The rotor components need to be balanced with the help of special balancing tooling. After the balancing is completed, the special balancing tooling is removed and the rotor components are assembled. After the assembly is completed, the balance state of the rotor components changes, which may easily cause the rotor blades to rub against the casing during the test, making it difficult to successfully reach the predetermined speed.

[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 this application. Summary of the Invention

[0009] The purpose of this application is to provide a casing containment test structure for an aircraft engine rotor component to overcome or alleviate at least one of the known technical defects.

[0010] The technical solution of this application is:

[0011] A casing containment test structure for an aircraft engine rotor component, comprising:

[0012] Receiver;

[0013] The rotor assembly is assembled in the casing;

[0014] a support plate connected to one end of the receiver and having a perforation therein;

[0015] A drive shaft is provided with a through-hole;

[0016] The transfer shaft is arranged to pass through the center of the rotor disc of the rotor component, and one end of the transfer shaft facing the support plate is connected to the end of the drive shaft facing the rotor component, and the outer wall of the transfer shaft has an annular transfer edge; the annular transfer edge is connected to the rotor disc of the rotor component;

[0017] The support cylinder is sleeved on the outer periphery of the driving shaft, one end of which is connected to the support plate, and the other end of which is sleeved on the outer periphery of the adapter shaft, with a gap left between the adapter shaft and the support cylinder;

[0018] The supporting shaft is a hollow structure and is sleeved on the other end of the transfer shaft with a gap left between the supporting shaft and the transfer shaft.

[0019] According to at least one embodiment of the present application, in the aforementioned aircraft engine rotor component casing containment test structure, the support plate has an annular support edge;

[0020] The annular supporting edge is butted against one end of the casing facing the supporting plate.

[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft engine rotor component casing containment test structure, the stoppers between the support plate and the support tube are positioned.

[0022] According to at least one embodiment of the present application, in the aforementioned aircraft engine rotor component casing containment test structure, the support tube is conical, with a hollow sidewall, and is shaped like a spoke wheel, with strain gauges bonded to the spokes;

[0023] The side wall of the support shaft is hollowed out in a squirrel cage shape, and strain gauges are bonded to the squirrel cage bars.

[0024] According to at least one embodiment of the present application, in the above-mentioned aircraft engine rotor component casing containment test structure, the hollowed-out portion of the upper side wall of the support shaft is close to the end of the support shaft facing the rotor wheel of the rotor component.

[0025] According to at least one embodiment of the present application, in the above-mentioned aircraft engine rotor component casing containment test structure, an annular protrusion is provided on the outer wall of the adapter shaft, and the annular protrusion is located inside the support shaft with a gap between the support shaft and the adapter shaft.

[0026] According to at least one embodiment of the present application, in the aforementioned aircraft engine rotor component casing containment test structure, the annular protrusion is located at the end of the support shaft facing one end of the rotor component rotor disc.

[0027] According to at least one embodiment of the present application, the aforementioned aircraft engine rotor component casing containment test structure further includes:

[0028] The support seat has a support hole thereon; one end of the support shaft facing away from the rotor wheel of the rotor component is inserted into the support hole.

[0029] According to at least one embodiment of the present application, in the above-mentioned aircraft engine rotor component casing containment test structure, the support shaft has an annular connecting edge, and the annular connecting edge is connected to the support seat. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a schematic diagram of the containment test structure of the rotor component casing of an existing aircraft engine;

[0031] Figure 2 Schematic diagram of a casing containment test structure for an aircraft engine rotor component provided in an embodiment of the present application;

[0032] Figure 3 is a schematic diagram of a transfer shaft provided in an embodiment of the present application;

[0033] Figure 4 is a schematic diagram of a support cylinder provided in an embodiment of the present application;

[0034] Figure 5 is a schematic diagram of a support shaft provided in an embodiment of the present application;

[0035] in:

[0036] 1-casing; 2-rotor component; 3-support plate; 4-drive shaft; 5-adapter shaft; 6-support cylinder; 7-support shaft; 8-support seat.

[0037] 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 should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0038] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease 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 of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0039] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0040] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" 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 a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0041] The following is combined with Figures 1 to 5 This application is described in further detail.

[0042] A casing containment test structure for an aircraft engine rotor component, comprising:

[0043] Receiver 1;

[0044] The rotor component 2 is assembled in the casing 1 and can be pre-notched or pre-buried with explosives at the predetermined breaking position where the rotor blade is expected to break and fly off;

[0045] A support plate 3, which can be fixed by a support structure, is connected to one end of the casing 1 and has a perforation thereon;

[0046] The driving shaft 4 is provided with a through hole;

[0047] The transfer shaft 5 is provided through the center of the rotor disc of the rotor component 2, and one end thereof facing the support plate 3 is connected to the end of the drive shaft 4 facing the rotor component 2. The outer wall of the transfer shaft 5 has an annular transfer edge; the annular transfer edge is connected to the rotor disc of the rotor component 2;

[0048] The support cylinder 6 is sleeved on the outer periphery of the drive shaft 4, one end of which is connected to the support plate 8, and the other end of which is sleeved on the outer periphery of the adapter shaft 5, with a gap between the adapter shaft 5 and the adapter shaft 5, which can be 1mm;

[0049] The support shaft 7 can be fixed by a support structure, is a hollow structure, and is sleeved on the other end of the adapter shaft 5, with a gap between the support shaft 7 and the adapter shaft 5, and the gap can be 5mm.

[0050] The aircraft engine rotor component casing containment test structure disclosed in the above embodiment is used to conduct an aircraft engine rotor component casing containment test. A drive mechanism such as a motor can be connected to the end of the drive shaft 4 facing away from the rotor wheel of the rotor component 2, and the rotor component 2 can be driven to rotate through the adapter shaft 5. The rotor blades that are predetermined to break and fly off are controlled to break and fly off at a predetermined breaking position at a predetermined speed and collide with the casing 1.

[0051] As for the aircraft engine rotor component casing containment test structure disclosed in the above embodiment, technical personnel in the field can understand that the two ends of the adapter shaft 5 designed to be connected to the rotor wheel of the rotor component 2 are constrained by the support tube 6 and the support shaft 7. When conducting the aircraft engine rotor component casing containment test, the rotor blades of the high-speed rotating rotor component 2 can be prevented from rubbing against the casing 1. In addition, before assembling the rotor component, a simply supported structure can be constructed using the drive shaft 4 and the adapter shaft 5 to balance the rotor component. After the balancing is completed, the rotor component 2, the drive shaft 4, and the adapter shaft 5 can be directly assembled as a whole without the need for disassembly, thereby effectively ensuring the balancing effect of the rotor component 2.

[0052] Regarding the aircraft engine rotor component casing containment test structure disclosed in the above embodiment, technical personnel in the field can also understand that the adapter shaft 5 is arranged to pass through the center of the rotor disc of the rotor component 2. When conducting the aircraft engine rotor component casing containment test, after the rotor blades break and fly off, they are subjected to the action of eccentric loads, and the two ends of the adapter shaft 5 rub against the support tube 6 and the support shaft 7, but the center of the rotor disc will not directly rub against the supporting component. This can reduce direct damage to the rotor component 2, avoid severe vibration that causes the rotor blades to fall off, and cause secondary damage to the casing 1.

[0053] In some optional embodiments, in the above-mentioned aircraft engine rotor component casing containment test structure, the support plate 3 has an annular support edge;

[0054] The annular supporting edge is butted against one end of the casing 1 facing the supporting plate 3 .

[0055] In some optional embodiments, in the above-mentioned aircraft engine rotor component casing containment test structure, the support plate 3 and the support tube 6 are positioned with a stop.

[0056] In some optional embodiments, in the aforementioned aircraft engine rotor component casing containment test structure, the support tube 6 is conical, with hollow sidewalls, and is shaped like a spoke wheel, with strain gauges bonded to the spokes;

[0057] The side wall of the support shaft 7 is hollowed out and has a squirrel cage shape, and strain gauges are bonded to the squirrel cage bars.

[0058] Regarding the aircraft engine rotor component casing containment test structure disclosed in the above embodiment, technical personnel in the field can also understand that the support tube 6 and the support shaft 7 are distributed on both sides of the rotor component 2. When conducting the aircraft engine rotor component casing containment test, when the rotor blades of the rotor component 2 break and fly off, the two ends of the adapter shaft 5 will impact the support tube 6 and the support shaft 7 under the action of the eccentric load. By using the strain gauges pasted on the spokes of the support tube 6 and the squirrel cage bars of the support shaft 7, the impact load of the fulcrums on both sides of the rotor component 2 can be measured, thereby accurately evaluating the eccentric load of the rotor wheel of the rotor component 2 when the rotor blades break and fly off.

[0059] In some optional embodiments, in the above-mentioned aircraft engine rotor component casing containment test structure, the hollowed-out portion of the upper side wall of the support shaft 7 is close to the end of the support shaft 7 facing the rotor wheel of the rotor component 2.

[0060] In some optional embodiments, in the above-mentioned aircraft engine rotor component casing containment test structure, the outer wall of the adapter shaft 5 has an annular protrusion, which is located inside the support shaft 7 and leaves a gap with the support shaft 7. The gap may be 5 mm. When conducting an aircraft engine rotor component casing containment test, when the rotor blades of the rotor component 2 break and fly off, the annular protrusion on the adapter shaft 5 will impact the support shaft 7 under the action of the eccentric load. The impact force is concentrated, which can ensure the accuracy of the strain gauge attached to the squirrel cage bar of the support shaft 7 in measuring the impact load of the corresponding side support point of the rotor component 2. In addition, the deformation of the annular protrusion has an energy absorption effect, which can reduce the vibration level of the rotor component 2 during the aircraft engine rotor component casing containment test.

[0061] In some optional embodiments, in the above-mentioned aircraft engine rotor component casing containment test structure, the annular protrusion is located at the end of the support shaft 7 facing the rotor wheel end of the rotor component 2.

[0062] In some optional embodiments, the above-mentioned aircraft engine rotor component casing containment test structure further includes:

[0063] The support seat 8 has a support hole thereon; one end of the support shaft 7 facing away from the rotor wheel of the rotor component 2 is inserted into the support hole.

[0064] In some optional embodiments, in the above-mentioned aircraft engine rotor component casing containment test structure, the support shaft 7 has an annular connecting edge, and the annular connecting edge is connected to the support seat 8.

[0065] 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 referred to in detail.

[0066] 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 replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A casing containment test structure for an aircraft engine rotor component, characterized in that: include: Receiver (1); A rotor component (2) is assembled in the casing (1); a support plate (3) connected to one end of the casing (1) and having a perforation thereon; A drive shaft (4) is provided passing through the perforation; A transfer shaft (5) is provided through the center of the rotor disc of the rotor component (2), and one end of the transfer shaft (5) facing the support plate (3) is connected to one end of the drive shaft (4) facing the rotor component (2), and an outer wall of the transfer shaft (5) has an annular transfer edge; the annular transfer edge is connected to the rotor disc of the rotor component (2); A support cylinder (6) is sleeved on the outer periphery of the drive shaft (4), one end of which is connected to the support plate (3), and the other end of which is sleeved on the outer periphery of the adapter shaft (5), with a gap of 1 mm between the adapter shaft (5); The support shaft (7) is a hollow structure and is sleeved on the other end of the transfer shaft (5), with a gap of 5 mm between the support shaft (7) and the transfer shaft (5); The support plate (3) has an annular support edge; The annular supporting edge is butted against one end of the casing (1) facing the supporting plate (3); An annular protrusion is provided on the outer wall of the adapter shaft (5), and the annular protrusion is located inside the support shaft (7), with a gap between the annular protrusion and the support shaft (7).

2. The aircraft engine rotor component casing containment test structure according to claim 1, characterized in that: The support plate (3) and the support tube (6) are positioned at a stop.

3. The aircraft engine rotor component casing containment test structure according to claim 2, characterized in that: The support cylinder (6) is conical, with a hollow side wall and a spoke wheel shape, and strain gauges are bonded to the spokes; The side wall of the support shaft (7) is hollowed out and is in the shape of a squirrel cage, and strain gauges are bonded to the squirrel cage bars.

4. The aircraft engine rotor component casing containment test structure according to claim 3, characterized in that: The hollowed-out portion of the upper side wall of the support shaft (7) is close to one end of the support shaft (7) facing the rotor wheel of the rotor component (2).

5. The aircraft engine rotor component casing containment test structure according to claim 4, characterized in that: Also includes: A support seat (8) is provided with a support hole; one end of the support shaft (7) facing away from the rotor wheel disc of the rotor component (2) is inserted into the support hole.

6. The aircraft engine rotor component casing containment test structure according to claim 5, characterized in that: The support shaft (7) has an annular connecting edge, and the annular connecting edge is connected to the support seat (8).

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