Magnetic control variable pitch joint debugging device, open rotor engine test piece and turboprop engine test piece

Abstract

The invention provides a magnetic control variable-pitch joint debugging device, an open rotor engine test piece and a turboprop engine test piece. The magnetic control variable-pitch joint debugging device comprises a rotating shaft; a propeller hub; the central part of the propeller hub is arranged on the rotating shaft in a sleeving manner, and a plurality of propeller fan mounting holes are formed in the outer side surface of the propeller hub; a plurality of paddle fans; each propeller fan is fixedly arranged on the propeller hub through the propeller fan mounting hole, and a bevel gear is arranged at the tail end of the inner side of each propeller fan; a first joint adjustment bevel gear; a second joint adjustment bevel gear; the first joint adjustment bevel gear and the second joint adjustment bevel gear are oppositely arranged, and a circumferential space is formed between the first joint adjustment bevel gear and the second joint adjustment bevel gear; the bevel gears are matched with the first joint adjustment bevel gear and the second joint adjustment bevel gear, and the bevel gears are separated from each other in the circumferential direction of the rotating shaft. An electromagnet and a magnetic block; the electromagnet and the magnetic block are arranged in the circumferential space between the first joint adjustment bevel gear and the second joint adjustment bevel gear and distributed in the circumferential direction.

Description

Technical Field

[0001] The present invention mainly relates to the field of aero-engines, and particularly relates to a magnetically controlled variable pitch joint adjustment device, an open rotor engine test piece, and a turboprop engine test piece. Background Art

[0002] During the research and development stage of an open rotor engine or a turboprop engine, it is necessary to conduct aerodynamic performance tests on the scaled-down propeller fan components to verify parameters such as thrust and power of the propeller fan at different pitch angles and different rotational speeds. Due to the use of scaled-down test forms, the traditional hydraulically actuated variable pitch system has problems such as too small component sizes and difficult oil supply after being directly scaled down in proportion, and it is difficult to be used in scaled-down tests.

[0003] Some existing propeller fan adjustment methods during the test process all require adjusting and fixing the propeller fan in sequence. For the scaled-down tests of a propeller with multiple propeller fans or an open rotor engine, this adjustment process increases the test time and reduces the test efficiency. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a magnetically controlled variable pitch joint adjustment device, an open rotor engine, and a turboprop engine test piece, so as to achieve rapid and effective adjustment of the pitch angle of the propeller fan during engine tests and improve the test efficiency.

[0005] To solve the above technical problem, the present invention provides a magnetically controlled variable pitch joint adjustment device, including: a rotating shaft; a propeller hub; the central part of the propeller hub is sleeved and installed on the rotating shaft, and a plurality of propeller fan mounting holes are provided on the outer side surface of the propeller hub; a plurality of propeller fans; each propeller fan is fixedly installed on the propeller hub through the propeller fan mounting hole, and the inner end of each propeller fan has a bevel gear; a first joint adjustment bevel gear; the central part of the first joint adjustment bevel gear is sleeved and installed on the rotating shaft; a second joint adjustment bevel gear; the central part of the second joint adjustment bevel gear is sleeved and installed on the rotating shaft; the first joint adjustment bevel gear and the second joint adjustment bevel gear are arranged oppositely, and a circumferential space is formed between the first joint adjustment bevel gear and the second joint adjustment bevel gear; the bevel gear at the inner end of each propeller fan cooperates with the first joint adjustment bevel gear and the second joint adjustment bevel gear, and the bevel gears at the inner ends of each propeller fan are separated from each other in the circumferential direction of the rotating shaft; an electromagnet and a magnetic block; the electromagnet and the magnetic block are installed in the circumferential space between the first joint adjustment bevel gear and the second joint adjustment bevel gear and are distributed circumferentially; the surfaces of the electromagnet and the magnetic block adjacent to the first joint adjustment bevel gear or the second joint adjustment bevel gear are respectively fixedly connected to the first joint adjustment bevel gear or the second joint adjustment bevel gear.

[0006] In an embodiment of the present invention, the electromagnet includes a power-off type electromagnet.

[0007] In an embodiment of the present invention, the magnetically controlled pitch linkage adjustment device further includes a conductive slip ring, which is sleeved on the rotating shaft and connected to the input electrical signal; the power-off electromagnet is connected to the conductive slip ring through an electrical connection line.

[0008] In an embodiment of the present invention, the contact surface between the electromagnet and the magnetic block is a rough mating surface.

[0009] In an embodiment of the present invention, a rough medium is included between the two opposite surfaces of the electromagnet and the magnetic block.

[0010] In an embodiment of the present invention, the magnetically controlled pitch linkage adjustment device further includes a control module, which is configured to provide a first control signal and a second control signal; when the conductive slip ring supplies power to the power-off electromagnet based on the first control signal, the power-off electromagnet does not have magnetism; the inner end of each paddle fan can rotate around the axis of the bevel gear at the inner end of the paddle fan to adjust the pitch of the paddle fan and realize the linkage adjustment of the pitches of multiple paddle fans at the same level; when the conductive slip ring does not supply power to the power-off electromagnet based on the second control signal, the power-off electromagnet has magnetism; there is a magnetic attraction force between the power-off electromagnet and the magnetic block, which hinders the relative rotation between the first linkage bevel gear and the second linkage bevel gear to lock the pitches of multiple paddle fans.

[0011] In an embodiment of the present invention, the magnetic block is an annular integral component or an annular component formed by combining multiple discrete components.

[0012] In an embodiment of the present invention, the electromagnet is an annular integral component or an annular component formed by combining multiple discrete components.

[0013] The present invention also provides an open rotor engine test piece, including the magnetically controlled pitch linkage adjustment device as described in any one of the preceding items.

[0014] In an embodiment of the present invention, the open rotor engine test piece includes two stages of paddle fans, and each stage includes multiple paddle fans.

[0015] The present invention also provides a turboprop engine test piece, including the magnetically controlled pitch linkage adjustment device as described in any one of the preceding items.

[0016] Compared with the prior art, the present invention has the following advantages: The technical solution of the present application can realize the linkage adjustment and precise locking of the pitch during the engine test process, so as to realize the rapid and efficient adjustment of the pitch of the paddle fan and improve the locking accuracy of the pitch, thereby improving the engine test efficiency. Description of the Drawings

[0017] The accompanying drawings are provided to offer a further understanding of the present application. They are incorporated into and form a part of this application. The accompanying drawings illustrate embodiments of the present application and, together with this specification, serve to explain the principles of the present application.

[0018] In the accompanying drawings:

[0019] Figure 1 It is a schematic diagram showing the composition of the magnetically controlled variable pitch coordinated control device according to an embodiment of the present application.

[0020] Figure 2 It is a schematic diagram showing the composition of the magnetically controlled variable pitch coordinated control device according to another embodiment of the present application.

[0021] Figure 3 It is a schematic diagram showing the structure of the open rotor engine test piece according to an embodiment of the present application.

[0022] Figure 4 It is a schematic diagram showing the pitch of the paddle fan of the magnetically controlled variable pitch coordinated control device according to an embodiment of the present application.

[0023] Figure 5 It is a schematic diagram showing the structure of the open rotor engine test piece according to an embodiment of the present application.

[0024] Figure 6 It is a schematic diagram showing the structure of the open rotor engine test piece according to another embodiment of the present application. Detailed implementation manners

[0025] To more clearly illustrate the technical solutions of the embodiments of the present application, the accompanying drawings required for the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some examples or embodiments of the present application. For those of ordinary skill in the art, without creative efforts, the present application can also be applied to other similar scenarios based on these drawings. Unless obvious from the language context or otherwise stated, the same reference numerals in the drawings represent the same structure or operation.

[0026] As shown in the present application and the claims, unless the context clearly indicates otherwise, words such as "a", "an", "one", and / or "the" are not specifically singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the clearly identified steps and elements, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0027] Unless otherwise specifically stated, the relative arrangements, numerical expressions, and numerical values of the components and steps described in these embodiments do not limit the scope of the present application. At the same time, it should be understood that for the convenience of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship.

[0028] In the description of the present application, it should be understood that the orientation or positional relationship indicated by orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom", etc. is usually based on the orientation or positional relationship shown in the drawings. This is only for the convenience of describing the present application and simplifying the description. Without contrary statements, these orientation words do not indicate or imply that the device or component referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation on the protection scope of the present application; the orientation words "inner, outer" refer to the inside and outside relative to the contour of each component itself.

[0029] In addition, it should be noted that the use of words such as "first", "second", etc. to limit components is only for the convenience of distinguishing the corresponding components. Without additional statements, the above words have no special meaning. Therefore, it should not be construed as a limitation on the protection scope of the present application. In addition, although the terms used in the present application are selected from well-known and commonly used terms, some of the terms mentioned in the specification of the present application may be selected by the applicant according to his or her judgment, and their detailed meanings are described in the relevant parts of the description herein. In addition, it is required to understand the present application not only through the actual terms used, but also through the meaning implied by each term.

[0030] Embodiments of the present application describe a magnetically controlled variable pitch joint adjustment device, an open rotor engine, and a turboprop engine test piece.

[0031] Figure 1 It is a schematic diagram of the composition of a magnetically controlled variable pitch joint adjustment device according to an embodiment of the present application. Figure 1 It is a sectional view. Refer to Figure 1 , the magnetically controlled variable pitch joint adjustment device 100 includes a rotating shaft 101, a hub 102, a plurality of paddle fans ( Figure 1 The paddle fan 103 is exemplarily marked in

[0032] In some embodiments, the central part of the hub 102 is sleeved and installed on the rotating shaft 101, and a plurality of paddle fan mounting holes ( Figure 1 The paddle fan mounting hole 122 is exemplarily marked in Figure 1 are provided on the outer side surface of the hub 102. Each paddle fan is fixedly installed on the hub 102 through the paddle fan mounting hole, and the inner end of each paddle fan has a bevel gear (

[0033] The central part of the first linkage adjusting bevel gear 105 is sleeved on the rotating shaft 101. The central part of the second linkage adjusting bevel gear 106 is also sleeved on the rotating shaft 101. The first linkage adjusting bevel gear 105 and the second linkage adjusting bevel gear 106 are arranged oppositely, and a circumferential space relative to the rotating shaft 101 is formed between the first linkage adjusting bevel gear 105 and the second linkage adjusting bevel gear 106. The bevel gears at the inner ends of each paddle fan cooperate with the first linkage adjusting bevel gear 105 and the second linkage adjusting bevel gear 106, and the bevel gears at the inner ends of each paddle fan are separated from each other in the circumferential direction of the rotating shaft 101.

[0034] The electromagnet 107 and the magnetic block 108 are arranged in the circumferential space between the first linkage adjusting bevel gear 105 and the second linkage adjusting bevel gear 106 and are distributed circumferentially; the surfaces of the electromagnet 107 and the magnetic block 108 adjacent to the first linkage adjusting bevel gear 105 or the second linkage adjusting bevel gear 106 are fixedly connected to the first linkage adjusting bevel gear 105 or the second linkage adjusting bevel gear 106 respectively. In Figure 1 the surface 107a of the electromagnet 107 adjacent to the first linkage adjusting bevel gear 105 is fixedly connected to the first linkage adjusting bevel gear 105, or is fixedly connected to the corresponding inner surface of the first linkage adjusting bevel gear 105, specifically, for example, by means of bolts, rivets, etc., or by means of adhesive. The surface 108a of the magnetic block 108 adjacent to the second linkage adjusting bevel gear 106 is fixedly connected to the second linkage adjusting bevel gear 106, or is fixedly connected to the corresponding inner surface of the second linkage adjusting bevel gear 106.

[0035] In some embodiments, the electromagnet 107 includes a power-off type electromagnet 112. The magnetically controlled pitch linkage adjusting device 100 further includes a conductive slip ring 109, which is sleeved on the rotating shaft 101 and is connected to the input electrical signal sg. The power-off type electromagnet 112 is connected to the conductive slip ring 109 through an electrical connection line 110. The conductive slip ring is an electrical component used to connect and transmit energy and signals for a rotating body. The characteristic of the power-off type electromagnet is that the magnetic force disappears in the energized state and the magnetic force is restored in the de-energized state.

[0036] In some embodiments, the magnetic block 108 is an annular integral component or is formed by combining a plurality of discrete components into an annular component. The electromagnet 107 is an annular integral component or is formed by combining a plurality of discrete components into an annular component. The contact surfaces of the electromagnet 107 and the magnetic block 108 are mating surfaces with rough treatment. In other embodiments, a rough medium is included between the two opposite surfaces of the electromagnet 107 and the magnetic block 108, so as to have greater contact friction.

[0037] Figure 2 It is a schematic diagram of the composition of the magnetically controlled pitch linkage adjusting device according to another embodiment of the present application. Figure 2 It is a cross-sectional view. In some embodiments, refer to Figure 2The magnetically controlled variable pitch joint adjustment device 200 further includes a control module 201, and the control module 201 is configured to provide a first control signal cr1 and a second control signal cr2.

[0038] When the conductive slip ring 109 supplies power to the de-energized electromagnet 112 based on the first control signal cr1, the de-energized electromagnet 112 is non-magnetic. The inner end of each propeller fan can rotate around the axial direction of the bevel gear at the inner end of the propeller fan to adjust the propeller fan pitch and realize the joint adjustment of the pitches of multiple propeller fans at the same level. When the conductive slip ring 109 does not supply power to the de-energized electromagnet 112 based on the second control signal, the de-energized electromagnet 112 is magnetic. There is a magnetic attraction between the de-energized electromagnet 112 and the magnetic block 108, which hinders the relative rotation between the first joint adjustment bevel gear 105 and the second joint adjustment bevel gear 106 to achieve the locking of the pitches of multiple propeller fans.

[0039] Figure 3 This is a schematic diagram of the structure of an open rotor engine test piece according to an embodiment of the present application. Figure 3 is a radial section view. Figure 3 As shown in FIG. 1 , the open rotor engine test piece 300 includes the aforementioned magnetically controlled variable pitch joint adjustment device. In some embodiments, the open rotor engine test piece includes two-stage propellers, and each stage includes a plurality of propellers. Figure 3 shows a first-stage propeller fan as an example, and the first-stage propeller fan includes propeller fan 103 and propeller fan 104. Each stage of propeller fan includes four, six or more propeller fans, for example.

[0040] For the open rotor engine test piece, when the pitch of the propeller fan needs to be adjusted, the control module 201 supplies power to the de-energized electromagnet 112 through the conductive slip ring 109 and the power supply wire 110, and the de-energized electromagnet 112 loses its magnetism, and the first joint adjustment bevel gear 105 and the second joint adjustment bevel gear 106 can rotate relatively. At this time, by adjusting a certain propeller fan to the target pitch, the pitch adjustment of all propeller fans at the same level is achieved, thereby achieving rapid adjustment of the propeller fan pitch.

[0041] When the pitch of the propeller fan needs to be locked or the pitch adjustment of the propeller fan ends, the control module 201 stops supplying power to the de-energized electromagnet 112 through the conductive slip ring 109 and the power supply wire 110, and the de-energized electromagnet 112 recovers its magnetism. The de-energized electromagnet 112 and the magnetic block 108 contact each other. Due to the effect of magnetic attraction, the rough surfaces of the two will generate friction torque, hindering the relative rotation of the first joint adjustment bevel gear 105 and the second joint adjustment bevel gear 106, and maintaining the pitch locked in the current state during the test. The magnetic block 108 can also be a magnetic panel, specifically a ferromagnetic panel or a magnetic panel made of other metal or non-metal materials.

[0042] ​​​During the test of the open rotor engine test piece, when the propfan speed of the open rotor engine scaled performance test piece or full-scale performance test piece is relatively high, the centrifugal torque generated is also relatively large. However, at this time, the centrifugal force is also relatively large, resulting in a relatively large frictional torque between the propfans 103 and 104 and the supporting surface of the hub 102, which will jointly maintain the pitch lock of the propfans with the coordinated adjustment bevel gears 105 and 106 in the current state. During the test, even if the conductive slip ring 109 fails, the power-off electromagnet 112 still has magnetism and can still maintain the propfans at the current pitch, thereby improving the test safety and the accuracy of pitch locking.

[0043] Figure 4 It is a pitch schematic diagram of the propfan of the magnetically controlled variable pitch coordinated adjustment device according to an embodiment of the present application. Refer to Figure 4 , the pitch of the propfan 401 is the included angle between the chord length 402 of the blade profile section at 75% of the blade height and the frontal line 403 (corresponding to the circumferential plane), and is usually represented by the symbol β 3 / 4 to represent. Figure 4 The direction R in

[0044] Figure 5 It is a schematic structural diagram of the open rotor engine test piece according to an embodiment of the present application. Figure 5 It is a radial cross-sectional view. Figure 5 For the open rotor engine test piece shown, after the coordinated adjustment of the propfans 103 and 104, the pitch changes, and thus the side view of the propfans also changes.

[0045] Figure 6 It is a schematic structural diagram of the open rotor engine test piece according to another embodiment of the present application. Figure 6 It is a radial cross-sectional view. Figure 6 For the open rotor engine test piece shown, the positions of the electromagnet 107 and the magnetic block 108 are swapped. Correspondingly, in Figure 6 , the surface 107a of the electromagnet 107 adjacent to the second coordinated adjustment bevel gear 106 is fixedly connected to the second coordinated adjustment bevel gear 106, or is referred to as fixedly connected to the corresponding inner surface of the second coordinated adjustment bevel gear 106. Specifically, for example, it is fixedly connected by means of bolts, rivets, etc., or is fixedly connected by means of glue. The surface 108a of the magnetic block 108 adjacent to the first coordinated adjustment bevel gear 105 is fixedly connected to the first coordinated adjustment bevel gear 105, or is referred to as fixedly connected to the corresponding inner surface of the first coordinated adjustment bevel gear 105.

[0046] Figure 3 , Figures 5 to 6 The open rotor engine test piece is, for example, a scaled-down open rotor engine test piece, or may also be a full-scale open rotor engine test piece.

[0047] The present invention also provides a turbine propeller engine test piece, which may include, for example, a first-stage propfan, and the first-stage propfan may include multiple propfans.

[0048] The magnetically controlled pitch joint adjustment device, open rotor engine and turbine propeller engine test piece of the present application can achieve rapid and efficient adjustment of the pitch during the engine test process, and improve the locking accuracy of the pitch, thereby improving the engine test efficiency.

[0049] The basic concepts have been described above. Obviously, for those skilled in the art, the above invention disclosure is only an example and does not constitute a limitation to the present application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements and corrections to the present application. Such modifications, improvements and corrections are proposed in the present application, so such modifications, improvements and corrections still fall within the spirit and scope of the exemplary embodiments of the present application.

[0050] At the same time, the present application uses specific terms to describe the embodiments of the present application. Such as "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0051] Some aspects of the present application can be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software can all be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor can be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors or combinations thereof. In addition, aspects of the present application may be embodied as a computer product located in one or more computer-readable media, which includes computer-readable program code.

[0052] Similarly, it should be noted that, in order to simplify the description of the present application disclosure and thus help the understanding of one or more invention embodiments, in the previous description of the embodiments of the present application, sometimes multiple features are merged into one embodiment, drawing or description thereof. However, this disclosure method does not mean that the features required by the object of the present application are more than those mentioned in the claims. In fact, the features of the embodiment are less than all the features of the above-disclosed single embodiment.

[0053] Although the present application has been described with reference to current specific embodiments, those of ordinary skill in the art should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions can be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the scope of the spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. A magnetically controlled variable pitch joint adjustment device, comprising: Rotating shaft; Propeller hub; The central part of the propeller hub is sleeve-mounted on the rotating shaft, and the outer side surface of the propeller hub is provided with a plurality of propeller fan mounting holes; A plurality of propellers; each propeller is fixedly mounted on the propeller hub through the propeller mounting hole, and the inner end of each propeller has a bevel gear; A first joint adjusting bevel gear; the central portion of the first joint adjusting bevel gear is sleeve-mounted on the rotating shaft; a second joint adjusting bevel gear; the central portion of the second joint adjusting bevel gear is sleeved and mounted on the rotating shaft; the first joint adjusting bevel gear and the second joint adjusting bevel gear are arranged opposite to each other, and a circumferential space is formed between the first joint adjusting bevel gear and the second joint adjusting bevel gear; the bevel gear at the inner end of each propeller cooperates with the first joint adjusting bevel gear and the second joint adjusting bevel gear, and the bevel gears at the inner end of each propeller are separated from each other in the circumferential direction of the rotating shaft; Electromagnet and magnetic block; the electromagnet and magnetic block are installed in the circumferential space between the first joint adjusting bevel gear and the second joint adjusting bevel gear, and are distributed along the circumferential direction; the surfaces of the electromagnet and magnetic block adjacent to the first joint adjusting bevel gear or the second joint adjusting bevel gear are fixedly connected to the first joint adjusting bevel gear or the second joint adjusting bevel gear respectively.

2. The magnetically controlled variable pitch joint adjustment device according to claim 1, characterized in that: The electromagnet comprises a de-energized electromagnet.

3. The magnetically controlled variable pitch joint adjustment device according to claim 2, characterized in that: It also includes a conductive slip ring, which is sleeved on the rotating shaft and connected to the input electrical signal; The de-energized electromagnet is connected to the conductive slip ring via an electrical connection line.

4. The magnetically controlled variable pitch joint adjustment device according to claim 1, characterized in that: The contact surface between the electromagnet and the magnetic block is a roughened fitting surface.

5. The magnetically controlled variable pitch joint adjustment device according to claim 1, characterized in that: A rough medium is included between two opposing surfaces of the electromagnet and the magnetic block.

6. The magnetically controlled variable pitch joint adjustment device according to claim 3, characterized in that: Also included is a control module configured to provide a first control signal and a second control signal; When the conductive slip ring supplies power to the de-energized electromagnet based on the first control signal, the de-energized electromagnet has no magnetism; the inner end of each propeller fan can rotate around the axial direction of the bevel gear at the inner end of the propeller fan to adjust the propeller fan pitch and realize the joint adjustment of the pitches of multiple propeller fans at the same level; When the conductive slip ring does not supply power to the de-energized electromagnet based on the second control signal, the de-energized electromagnet is magnetic; there is a magnetic attraction force between the de-energized electromagnet and the magnetic block, which hinders the relative rotation between the first coupling bevel gear and the second coupling bevel gear to achieve locking of the pitch of multiple propellers.

7. The magnetically controlled variable pitch joint adjustment device according to claim 1, characterized in that: The magnetic block is an annular integral component or is formed by combining a plurality of discrete components to form an annular component.

8. The magnetically controlled variable pitch joint adjustment device according to claim 1, characterized in that: The electromagnet is an annular integral component or is an annular component formed by combining a plurality of discrete components.

9. An open rotor engine test piece, comprising the magnetically controlled variable pitch joint adjustment device according to any one of claims 1 to 8.

10. The open rotor engine test piece according to claim 9, characterized in that: The open rotor engine test piece includes two stages of propfans, and each stage includes a plurality of propfans.

11. A turboprop engine test piece, comprising the magnetically controlled variable pitch joint adjustment device according to any one of claims 1 to 8.

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