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

Abstract

The application provides a magnetic control variable pitch joint debugging device, an open rotor engine test piece and a turbo propeller engine test piece, which comprises a rotating shaft, a hub, a central part of the hub is sleeved and arranged on the rotating shaft, an outer side surface of the hub is provided with a plurality of paddle fan mounting holes, a plurality of paddle fans, each paddle fan is fixedly arranged on the hub through the paddle fan mounting hole, an inner side end of each paddle fan is provided with a bevel gear, a first joint debugging bevel gear, a second joint debugging bevel gear, the first joint debugging bevel gear and the second joint debugging bevel gear are oppositely arranged, and a circumferential space is formed between the first joint debugging bevel gear and the second joint debugging bevel gear, the bevel gears are matched with the first joint debugging bevel gear and the second joint debugging bevel gear, and each bevel gear is 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 debugging bevel gear and the second joint debugging bevel gear and are distributed in the circumferential direction.

Description

TECHNICAL FIELD

[0001] The present application mainly relates to the field of aero-engines, and particularly relates to a magnetic control variable-pitch joint adjustment device, an open rotor engine test piece and a turboprop engine test piece. BACKGROUND

[0002] During the development stage of an open rotor engine or a turboprop engine, aerodynamic performance tests need to be carried out on a scaled-down propeller-fan test piece to verify the thrust, power and other parameters of the propeller-fan at different pitches and different rotating speeds. Since the scaled-down test form is adopted, the traditional hydraulic actuation variable-pitch system directly scaled down according to the proportion has problems such as too small size of components, difficulty in oil supply and the like, and is difficult to be used for scaled-down tests.

[0003] Some existing propeller-fan adjustment modes in the test process all need to adjust and fix the propeller-fan in sequence, and for scaled-down tests of multiple propeller-fans or open rotor engines, the adjustment process increases the test time and reduces the test efficiency. SUMMARY

[0004] The technical problem to be solved by the present application is to provide a magnetic control variable-pitch joint adjustment device, an open rotor engine and a turboprop engine test piece, to realize rapid and effective adjustment of the pitch of the propeller-fan during the engine test, and to improve the test efficiency.

[0005] To solve the above technical problem, the present application provides a magnetic control variable-pitch joint adjustment device, comprising: a rotating shaft; a hub; the central part of the hub is sleeved and arranged on the rotating shaft, and the outer side of the hub is provided with a plurality of propeller-fan mounting holes; a plurality of propeller-fans; each propeller-fan is fixedly arranged on the hub through the propeller-fan mounting hole, and the inner end of each propeller-fan is provided with a bevel gear; a first joint adjustment bevel gear; the central part of the first joint adjustment bevel gear is sleeved and arranged on the rotating shaft; a second joint adjustment bevel gear; the central part of the second joint adjustment bevel gear is sleeved and arranged on the rotating shaft; 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 at the inner ends of each propeller-fan are matched 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 arranged in the circumferential space between the first joint adjustment bevel gear and the second joint adjustment bevel gear, and are distributed in the circumferential direction; the surfaces of the electromagnet and the magnetic block close to the first joint adjustment bevel gear or the second joint adjustment bevel gear are fixedly connected with the first joint adjustment bevel gear or the second joint adjustment bevel gear, respectively.

[0006] In an embodiment of the present application, the electromagnet comprises a de-energized electromagnet.

[0007] In an embodiment of the present application, the magnetic control variable pitch joint debugging device further comprises a conductive slip ring sleeved on the rotating shaft and connected to the input electric signal; the de-energized electromagnet is connected to the conductive slip ring through an electric connection line.

[0008] In an embodiment of the present application, the contact surface of the electromagnet and the magnetic block is a roughened fitting surface.

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

[0010] In an embodiment of the present application, the magnetic control variable pitch joint debugging device further comprises 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 can rotate around the shaft of the bevel gear at the inner end of the propeller, realizing the adjustment of the pitch of the propeller and the joint debugging of the pitches of multiple propellers 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 has magnetism; the de-energized electromagnet and the magnetic block have magnetic attraction, hindering the relative rotation between the first joint debugging bevel gear and the second joint debugging bevel gear, to realize the locking of the pitches of multiple propellers.

[0011] In an embodiment of the present application, the magnetic block is a ring-shaped integral component or a ring-shaped component formed by combining multiple separate components.

[0012] In an embodiment of the present application, the electromagnet is a ring-shaped integral component or a ring-shaped component formed by combining multiple separate components.

[0013] The present application also provides an open rotor engine test piece comprising the magnetic control variable pitch joint debugging device according to any one of the preceding items.

[0014] In an embodiment of the present application, the open rotor engine test piece comprises two levels of propellers, and each level comprises multiple propellers.

[0015] The present application also provides a turboprop engine test piece comprising the magnetic control variable pitch joint debugging device according to any one of the preceding items.

[0016] Compared with the prior art, the present application has the following advantages: the technical solution of the present application can realize the joint debugging and accurate locking of the pitch during the engine test process, thereby realizing the rapid and efficient adjustment of the pitch of the propeller and improving the locking accuracy of the pitch, thereby improving the engine test efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0017] The accompanying drawings are included to provide a further understanding of the present application and are incorporated in and constitute apart of this application, illustrate embodiments of the present application and together with the description serve to explain the principles of the present application.

[0018] In the drawings:

[0019] Figure 1 is a schematic diagram of a magnetic control variable pitch joint debugging device according to an embodiment of the present application.

[0020] Figure 2 is a schematic diagram of a magnetic control variable pitch joint debugging device according to another embodiment of the present application.

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

[0022] Figure 4 is a schematic diagram of a pitch of a propeller fan of a magnetic control variable pitch joint debugging device according to an embodiment of the present application.

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

[0024] Figure 6 is a schematic diagram of a structure of an open rotor engine test piece according to another embodiment of the present application. DETAILED DESCRIPTION

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiment description will be briefly introduced as follows. Obviously, the drawings in the following description are only some examples or embodiments of the present application, and for those skilled in the art, the present application can also be applied to other similar scenarios without creative labor, unless it is obvious from the language environment or otherwise stated. In the drawings, the same reference numerals represent the same structures or operations unless the context clearly indicates otherwise.

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

[0027] Unless specifically stated otherwise, the relative arrangement of the components and steps illustrated in these embodiments, numerical expressions, and numerical values do not limit the scope of the present application. At the same time, it should be understood that the sizes of the various parts shown in the drawings are not drawn in accordance with the actual proportional relationship.

[0028] In the description of the present application, it should be understood that the orientation words such as "front, back, up, down, left, right", "transverse, vertical, perpendicular, horizontal" and "top, bottom" and the like indicated orientation or position relationship is generally based on the orientation or position relationship shown in the drawings, only for the convenience of describing the present application and simplifying the description, without making the opposite statement, these orientation words do not indicate and imply that the device or element referred to must have a particular orientation or be constructed and operated in a particular orientation, therefore, it cannot be understood as a limitation on the scope of protection of the present application; the orientation words "inner, outer" refer to the inner and outer of the contour of each component itself.

[0029] In addition, it should be noted that the use of "first", "second" and the like to limit the parts is only for the convenience of distinguishing the corresponding parts, and the above words have no special meaning unless otherwise stated, therefore, it cannot be understood as a limitation on the scope of protection of the present application. In addition, although the terms used in the present application are selected from the commonly known and used terms, some terms mentioned in the specification of the present application may be selected by the applicant according to his or her judgment, and the detailed meaning of each term is explained in the relevant part of the description. In addition, the present application is required to be understood not only by the actual terms used, but also by the meaning implied by each term.

[0030] The embodiment of the present application describes a magnetic control variable pitch joint debugging device, an open rotor engine and a turboprop engine test piece.

[0031] Figure 1 is a schematic diagram of the magnetic control variable pitch joint debugging device according to an embodiment of the present application. Figure 1 is a sectional view. Referring to Figure 1 , the magnetic control variable pitch joint debugging device 100 comprises a rotating shaft 101, a hub 102, a plurality of fan blades (for example, the fan blades 103 are exemplarily indicated in the drawings), a first joint debugging bevel gear 105, a second joint debugging bevel gear 106, an electromagnet 107 and a magnetic block 108. Figure 1

[0032] In some embodiments, the central part of the hub 102 is sleeved and installed on the rotating shaft 101, and the outer side of the hub 102 is provided with a plurality of fan blade mounting holes (for example, the fan blade mounting hole 122 is exemplarily indicated in the drawings). Figure 1 Each fan blade is fixedly installed on the hub 102 through the fan blade mounting hole, and the inner end of each fan blade has a bevel gear (for example, the inner end of the fan blade 103 has a bevel gear 103a, which is exemplarily indicated in the drawings). Figure 1

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

[0034] The electromagnets 107 and the magnetic blocks 108 are arranged in the circumferential space between the first pitch adjusting bevel gear 105 and the second pitch adjusting bevel gear 106 and are distributed in the circumferential direction. The surfaces of the electromagnets 107 and the magnetic blocks 108 adjacent to the first pitch adjusting bevel gear 105 or the second pitch adjusting bevel gear 106 are fixedly connected with the first pitch adjusting bevel gear 105 or the second pitch adjusting bevel gear 106, respectively. Figure 1 In some embodiments, the surface 107a of the electromagnet 107 adjacent to the first pitch adjusting bevel gear 105 is fixedly connected with the first pitch adjusting bevel gear 105, or is fixedly connected with the corresponding inner surface of the first pitch adjusting bevel gear 105, for example, by means of bolts, rivets or adhesive.

[0035] In some embodiments, the electromagnets 107 include loss-of-field electromagnets 112. The magnetic pitch control and pitch adjusting device 100 further includes a conductive slip ring 109 sleeved on the rotating shaft 101 and connected with the input electric signal sg. The loss-of-field electromagnets 112 are connected with the conductive slip ring 109 through the electric connection lines 110. The conductive slip ring is an electrical component for connecting and transmitting energy and signals for a rotating body. The loss-of-field electromagnets have the characteristic that the magnetic force disappears in the energized state and recovers in the de-energized state.

[0036] In some embodiments, the magnetic blocks 108 are annular integral components or are formed by combining a plurality of separate components into annular components. The electromagnets 107 are annular integral components or are formed by combining a plurality of separate components into annular components. The contact surfaces of the electromagnets 107 and the magnetic blocks 108 are roughened and matched. In other embodiments, roughened medium is included between the two opposite surfaces of the electromagnets 107 and the magnetic blocks 108, so as to have greater contact friction.

[0037] Figure 2 is a schematic diagram of the composition of the magnetic pitch control and pitch adjusting device according to another embodiment of the present application. Figure 2 is a cross-sectional view. In some embodiments, reference is made to Figure 2The magnetic control variable pitch joint device 200 further comprises a control module 201, which is configured to provide a first control signal cr1 and a second control signal cr2.

[0038] When the electrically conductive slip ring 109 supplies power to the power-off electromagnet 112 based on the first control signal cr1, the power-off electromagnet 112 has no magnetism. The inner end of each propeller can rotate around the shaft of the bevel gear at the inner end of the propeller, achieving adjustment of the pitch of the propeller and joint adjustment of the pitch of multiple propellers at the same level. When the electrically conductive slip ring 109 does not supply power to the power-off electromagnet 112 based on the second control signal, the power-off electromagnet 112 has magnetism. The power-off electromagnet 112 has magnetic attraction with the magnetic block 108, hindering the relative rotation between the first joint adjustment bevel gear 105 and the second joint adjustment bevel gear 106, to achieve locking of the pitch of multiple propellers.

[0039] Figure 3 is a structural schematic diagram of an open rotor engine test piece according to an embodiment of the present application. Figure 3 is a radial sectional view. As shown in Figure 3 , the open rotor engine test piece 300 comprises the aforementioned magnetic control variable pitch joint device. In some embodiments, the open rotor engine test piece comprises two levels of propellers, and each level comprises multiple propellers. Figure 3 An exemplary level of propellers is shown in

[0040] For the open rotor engine test piece, when it is necessary to adjust the pitch of the propellers, the control module 201 supplies power to the power-off electromagnet 112 through the electrically conductive slip ring 109 and the power supply wire 110, the power-off electromagnet 112 loses magnetism, and the first joint adjustment bevel gear 105 and the second joint adjustment bevel gear 106 can rotate relative to each other. At this time, by adjusting a certain propeller to a target pitch, the pitch of all propellers at the same level is adjusted, thereby achieving rapid adjustment of the pitch of the propellers.

[0041] When the pitch of the propellers needs to be locked or the adjustment of the pitch of the propellers is completed, the control module 201 stops supplying power to the power-off electromagnet 112 through the electrically conductive slip ring 109 and the power supply wire 110, the power-off electromagnet 112 regains magnetism, and the power-off electromagnet 112 and the magnetic block 108 contact each other. Due to the magnetic attraction, a friction torque is generated between the rough surfaces of the two, hindering the relative rotation of the first joint adjustment bevel gear 105 and the second joint adjustment bevel gear 106, and maintaining the current state of the pitch lock during the test. The magnetic block 108 can also be a magnetic panel, which can be a ferromagnetic panel or a magnetic panel made of other metal or non-metal materials.

[0042] In the process of testing the open-rotor engine test piece, when the paddle-fan speed of the open-rotor engine scale performance test piece or full-size performance test piece is high, the centrifugal torque generated is also large, but at this time the centrifugal force is also large, so the friction torque between the paddle-fan 103, the paddle-fan 104 and the supporting surface of the paddle hub 102 is also large, thereby maintaining the current state of the paddle-fan pitch together with the gear coupling cone gears 105, 106. In the process of testing, even if the conductive slip ring 109 fails, the loss of power type electromagnet 112 still has magnetism and can still maintain the current paddle-fan pitch, thereby improving the test safety and the accuracy of the paddle-fan pitch locking.

[0043] Figure 4 is a schematic diagram of the paddle-fan pitch of the magnetic control variable-pitch gear coupling device of an embodiment of the present application. Referring to Figure 4 , the paddle-fan pitch of the paddle-fan 401 is the angle between the chord length 402 of the airfoil section at 75% of the blade height and the camber line 403 (corresponding to the circumferential plane), which is usually represented by the symbol 3 / 4 . Figure 4 The direction R in indicates the flight direction corresponding to the rotation direction of the engine paddle-fan.

[0044] Figure 5 is a structural schematic diagram of an open-rotor engine test piece of an embodiment of the present application. Figure 5 is a radial sectional view. Figure 5 The open-rotor engine test piece shown in the figure, after the paddle-fan 103 and the paddle-fan 104 are coupled, the paddle-fan pitch changes, and thus the side view of the paddle-fan also changes.

[0045] Figure 6 is a structural schematic diagram of an open-rotor engine test piece of another embodiment of the present application. Figure 6 is a radial sectional view. Figure 6 The open-rotor engine test piece shown in the figure, the positions of the electromagnet 107 and the magnetic block 108 are exchanged. Correspondingly, in Figure 6 , the surface 107a of the electromagnet 107 adjacent to the second gear coupling cone gear 106 is fixedly connected with the second gear coupling cone gear 106, or is fixedly connected with the corresponding inner side surface of the second gear coupling cone gear 106, for example, fixedly connected by means of bolts, rivets, etc., or fixedly connected by means of adhesive. The surface 108a of the magnetic block 108 adjacent to the first gear coupling cone gear 105 is fixedly connected with the first gear coupling cone gear 105, or is fixedly connected with the corresponding inner side surface of the first gear coupling cone gear 105.

[0046] Figure 3 , Figures 5 to 6 is an open-rotor engine test piece, for example, a scale open-rotor engine test piece, or a full-size open-rotor engine test piece.

[0047] The present application also provides a turboprop engine test piece, for example, including a first stage propfan, which can include a plurality of propfans.

[0048] The magnetic control variable pitch joint debugging device, open rotor engine and turboprop engine test piece of the present application can realize rapid and efficient adjustment of the pitch during engine test, improve the locking precision of the pitch, and thus improve the engine test efficiency.

[0049] The foregoing has described the basic concepts, and it is obvious that the above-mentioned disclosure of the application is only as an example and does not constitute a limitation on the present application. Although it is not explicitly stated here, those skilled in the art can make various modifications, improvements and corrections to the present application. Such modifications, improvements and corrections are suggested in the present application, so such modifications, improvements and corrections still belong to the spirit and scope of the exemplary embodiments of the present application.

[0050] At the same time, specific words are used in the present application to describe the embodiments of the present application. As "one embodiment", "an embodiment", and / or "some embodiments" means 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 "an embodiment" or "one embodiment" or "an alternative embodiment" mentioned in different places in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be properly combined.

[0051] Some aspects of the present application can be completely executed by hardware, completely executed by software (including firmware, resident software, microcode, etc.), or executed by a combination of hardware and software. The above hardware or software can be referred to as "data block", "module", "engine", "unit", "component" or "system". The processor can be one or more application specific integrated circuits (ASIC), digital signal processors (DSP), digital signal processing devices (DAPD), programmable logic devices (PLD), field programmable gate arrays (FPGA), processors, controllers, microcontrollers, microprocessors or combinations thereof. In addition, aspects of the present application can be embodied as a computer product located in one or more computer readable media, including computer readable program code.

[0052] Similarly, it should be noted that, in order to simplify the expression of the present application and to help understand one or more embodiments of the application, in the foregoing description of the embodiments of the present application, various features are sometimes combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the present application are more than the features mentioned in the claims. In fact, the features of the embodiment are less than all the features of the disclosed single embodiment.

[0053] While the application has been described with reference to current embodiments, it will be understood by those skilled in the art that various equivalent substitutions and modifications can be made to the embodiments without departing from the spirit of the application, and it is intended that the application encompass any and all such substitutions and modifications within its spirit and scope.

Claims

1. A magnetically controlled variable pitch adjustment device, comprising: Rotating shaft; propeller hub; The center part of the propeller hub is sleeved and mounted on the rotating shaft, and the outer side of the propeller hub is provided with multiple propeller fan mounting holes; Multiple propellers; each propeller is fixedly mounted on the propeller hub through the propeller mounting hole, and each propeller has a bevel gear at its inner end; The first adjusting bevel gear; the central part of the first adjusting bevel gear is sleeved and mounted on the rotating shaft; The second bevel gear; the central part of the second bevel gear is sleeved on the rotating shaft; the first bevel gear and the second bevel gear are arranged opposite to each other and form a circumferential space between the first bevel gear and the second bevel gear; the bevel gear at the inner end of each blade is engaged with the first bevel gear and the second bevel gear, and the bevel gear at the inner end of each blade is separated from each other in the circumferential direction of the rotating shaft. An electromagnet and a magnetic block are provided; the electromagnet and the magnetic block are installed in the circumferential space between the first and second bevel gears and distributed circumferentially; the surfaces of the electromagnet and the magnetic block adjacent to the first or second bevel gear are fixedly connected to the first or second bevel gear respectively.

2. The magnetically controlled variable pitch adjustment device according to claim 1, characterized in that, The electromagnets include de-energized electromagnets.

3. The magnetically controlled variable pitch 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 wire.

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

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

6. The magnetically controlled variable pitch adjustment device according to claim 3, characterized in that, It also includes 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 is not magnetic; the inner end of each blade can rotate around the axial direction of the bevel gear at the inner end of the blade to adjust the blade pitch and achieve coordinated adjustment of the blade pitch of multiple blades in the same stage. 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 between the de-energized electromagnet and the magnetic block, which hinders the relative rotation between the first and second bevel gears, so as to lock the pitch of the multiple propellers.

7. The magnetically controlled variable pitch adjustment device according to claim 1, characterized in that, The magnetic block is a ring-shaped integral component or a ring-shaped component formed by merging multiple discrete components.

8. The magnetically controlled variable pitch adjustment device according to claim 1, characterized in that, The electromagnet is either a ring-shaped integral component or a ring-shaped component formed by merging multiple discrete components.

9. An open rotor engine test piece, comprising the magnetically controlled variable pitch adjustment device as described in any one of claims 1-8.

10. The open rotor engine test piece according to claim 9, characterized in that, The open rotor engine test piece includes two stages of propellers, and each stage includes multiple propellers.

11. A turboprop engine test piece, comprising the magnetically controlled variable pitch adjustment device as described in any one of claims 1-8.

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