An embedded lubricating nozzle for an aero-engine gearbox and the gearbox

Abstract

The present invention relates to the field of lubricating nozzles for aeroengine gearboxes, and specifically discloses an embedded lubricating nozzle for an aeroengine gearbox, which comprises a cavity structure. A first sealing structure, a nozzle orifice, a second sealing structure and a third sealing structure are sequentially arranged on the cavity structure. The first sealing structure is used for sealing the connection between the cavity structure and one end of the aeroengine gearbox casing. The nozzle orifice is used for multi-point lubrication of the meshing points in the gearbox. The second sealing structure is used for sealing the connection between the cavity structure and the other end of the aeroengine gearbox casing. A positioning structure is further arranged on the cavity structure, and the positioning structure is used for guiding the embedding direction when the lubricating nozzle is embedded into the aeroengine gearbox casing and stopping the installed lubricating nozzle. This nozzle can provide multi-point lubrication for the aeroengine gearbox, and at the same time, it is convenient to install, occupies a small space and has high reliability during operation.

Description

Technical Field

[0001] The present invention relates to the field of lubricating nozzles for aeroengine gearboxes, and specifically to an embedded lubricating nozzle for an aeroengine gearbox and a gearbox. Background Art

[0002] Aeroengine gearboxes are characterized by high rotational speeds and a wide rotational speed range. The gears and bearings in the gearbox require lubrication and cooling with lubricating oil during operation. The commonly used lubrication methods for aeroengine gearboxes are direct injection and oil mist lubrication. However, when the gearbox includes both a power turbine reducer and an accessory drive reducer, due to the large number of gears and bearings and the need to lubricate each gear meshing point and bearing in the power turbine reducer, the number of injection lubrication points is large.

[0003] Currently, for the lubrication points that need to be injected in the above aeroengine gearboxes, the nozzle injection method is generally used. The nozzle is a part with a lubricating oil passage, on which injection holes are designed, and it is generally installed at a position that can communicate with the main lubricating oil supply circuit. The nozzle generally has a flange mounting structure and is fixed to the casing by screws, so that continuous oil supply can be provided to the determined injection points during engine operation. For a single-point injection nozzle (i.e., there is only one injection hole on it), sometimes threads are designed on it and it is screwed into a threaded hole that communicates with the main lubricating oil supply circuit in a specific direction. For the injection holes with a flange mounting structure, due to the need for screw fastening, screw mounting holes need to be designed and space needs to be provided for the screw mounting holes on the casing. When the number of injection points is large (such as the case where the above-mentioned gearbox includes both a power turbine reducer and an accessory drive reducer), it is often difficult to design screw fastening positions for installing a large number of nozzles. Especially when the positions of multiple injection points are relatively concentrated and cannot be achieved through the design of injection holes on a single nozzle, the above difficulties will be more prominent. For the nozzle with threads, in order to ensure the reliability of the nozzle installation, glue is generally applied during installation, which increases the complexity of the assembly, and when the glue is not selected reasonably, there is a risk of the nozzle falling off in a vibration environment. Moreover, the casing of the aeroengine gearbox is generally made of aluminum alloy or magnesium alloy, and the threaded holes are easily damaged, and it is not easy to repair once the threaded hole is damaged.

[0004] In addition, the lubricating nozzle for the aeroengine gearbox should be able to provide sufficient lubricating oil for the lubrication and cooling of the gears and the injection position of the nozzle should not change due to the influence of vibration during engine operation. The nozzle should also provide a passage for the flow of lubricating oil without affecting the engine hydraulic actuator. Summary of the Invention

[0005] The object of the present invention is to provide an embedded lubrication nozzle for an aero-engine gearbox, which can provide multi-point lubrication for the above-mentioned aero-engine gearbox with a large number of lubrication points, and at the same time is convenient to install, occupies a small space and has high reliability during operation.

[0006] The object of the present invention can be achieved by the following technical solutions:

[0007] An embedded lubrication nozzle for an aero-engine gearbox, comprising a cavity structure, on which a first sealing structure, a nozzle, a second sealing structure and a third sealing structure are successively arranged. The first sealing structure is used for sealing the connection between the cavity structure and one end of the engine gearbox casing. The nozzle is used for multi-point lubrication of the meshing points in the gearbox. The second sealing structure is used for sealing the connection between the cavity structure and the other end of the engine gearbox casing, preventing the oil on the oil path a of the engine gearbox casing from leaking into the engine gearbox, and preventing the oil in the gearbox from being reversely introduced into the oil path a to contaminate related components. The third sealing structure is used for sealing the entrance of the installation cavity on the engine gearbox casing for embedding the lubrication nozzle. A positioning structure is also arranged on the cavity structure, and the positioning structure is used for guiding the embedding direction when the lubrication nozzle is embedded into the engine gearbox casing and stopping the lubrication nozzle after installation.

[0008] In a further aspect, the nozzle includes a first protrusion connected to the cavity structure, and a plurality of oil injection holes communicating with the cavity structure are opened on the first protrusion.

[0009] In a further aspect, the first sealing structure includes a first sealing shaft and a first shoulder. The first shoulder is connected to one end of the first sealing shaft close to the nozzle. A first sealing groove is opened at a position of the first sealing shaft close to the first shoulder. By connecting a sealing ring on the first sealing groove, it is used to form a seal between the first sealing shaft and the installation cavity.

[0010] In a further aspect, the second sealing structure includes a second sealing shaft and a second shoulder. The second shoulder is connected to one end of the second sealing shaft far from the nozzle. A second sealing groove is opened at a position of the second sealing shaft close to the second shoulder. By connecting a sealing ring on the second sealing groove, it is used to form a seal between the second sealing shaft and the installation cavity.

[0011] In a further aspect, the third sealing structure includes a third sealing shaft. The third sealing shaft is connected to the cavity structure far from the second sealing structure. The third sealing shaft is used to match the end of the installation cavity. A third sealing groove is arranged on the third sealing shaft. By connecting a sealing ring on the third sealing groove, it is used to form a seal between the third sealing shaft and the installation cavity.

[0012] In a further solution, the positioning structure includes a second protrusion, which is connected to one end of the cavity structure away from the first sealing structure. By only opening a stop groove matching the second protrusion on the installation cavity of the engine gearbox casing, it can be used to position the lubrication nozzle of the aero-engine gearbox on the engine gearbox casing. Preferably, the second protrusion can be arranged on the third sealing structure.

[0013] In a further solution, an avoidance groove is provided at the connection between the second protrusion and the cavity structure.

[0014] In a further solution, a branch oil passage hole is provided on the cavity structure between the second sealing structure and the third sealing structure.

[0015] In a further solution, chamfers facilitating their insertion into the installation cavity are provided on both the first sealing structure and the second sealing structure.

[0016] In a further solution, a threaded hole is provided at one end of the cavity structure away from the first sealing structure, which is used to pull out and remove the embedded aero-engine gearbox lubrication nozzle during installation.

[0017] Based on the same inventive principle or concept, the present invention also provides an embedded aero-engine gearbox, which includes an engine gearbox casing, a sealing cover and the above-mentioned lubrication nozzle. An installation cavity for the lubrication nozzle to be embedded and matched is opened on the engine gearbox casing, and the sealing cover is used to seal and connect the lubrication nozzle embedded in the installation cavity to the engine gearbox casing.

[0018] In a further solution, an annular sealing groove is opened on the sealing cover, and the annular sealing groove can form an end seal with the cavity structure through a sealing ring, ensuring that the lubricating oil reliably flows into the oil passage c in the sealing cover from the threaded hole on the nozzle without leakage.

[0019] In a further solution, the sealing ring is preferably an O-ring.

[0020] The beneficial effects of the present invention are as follows:

[0021] 1. By integrating multiple nozzles on the embedded cavity structure, corresponding to the gear lubrication points and bearing lubrication points with lubrication, realizing self-positioning through the positioning structure, and locking through the sealing cover of the gearbox. Compared with the existing multi-flange and multi-nozzle setting methods, the nozzle positioning of the present invention does not require the use of installation flanges and threaded fastening, saving the number of parts and installation space, and saving the work of controlling the tightening torque.

[0022] 2. The use of a stop groove and a second protrusion that can avoid interference, a pull-out thread for convenient disassembly, and a guiding structure for convenient installation makes the assembly and disassembly efficiency higher.

[0023] 3. The extraction and disassembly threaded hole serves as an oil passage at the same time, and together with the positioning structure, it realizes the embedded installation of the nozzle, saves the installation space, and enables the combined use with hydraulic actuating parts.

[0024] 4. The simultaneous use of multiple O-ring seals enables the nozzle to have the functions of spraying lubricating oil and conveying lubricating oil at the same time. Moreover, the combined use of the axial compression method and the radial compression method of the O-ring seals significantly reduces the resistance during installation and disassembly while ensuring reliable sealing and accurate positioning. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0026] Figure 1 It is a schematic diagram of an embedded lubricating nozzle for an aeroengine gearbox in an embodiment of the present invention;

[0027] Figure 2 It is a connection schematic diagram of the relief groove in an embodiment of the present invention;

[0028] Figure 3 It is Figure 2 the sectional view taken along line A-A in

[0029] Figure 4 It is Figure 2 the partial sectional view taken along line B-B in

[0030] Figure 5 It is a connection schematic diagram of the engine gearbox casing and the sealing cover in an embodiment of the present invention;

[0031] Figure 6 It is Figure 5 the partial sectional view taken along line C-C in

[0032] Figure 7 It is Figure 6 the partial sectional view taken along line D-D in

[0033] Figure 8 It is an exploded schematic diagram of the installation location of an embedded lubricating nozzle for an aeroengine gearbox in an embodiment of the present invention;

[0034] Figure 9 It is Figure 6 the partial schematic diagram at position F in

[0035] In the figure: 1. Cavity structure; 11. Branch oil through-hole; 12. Threaded hole; 2. First sealing structure; 21. First sealing shaft; 211. First sealing groove; 22. First shaft shoulder; 3. Nozzle; 31. First protrusion; 311. Oil injection hole; 4. Second sealing structure; 41. Second sealing shaft; 411. Second sealing groove; 42. Second shaft shoulder; 5. Third sealing structure; 51. Third sealing shaft; 511. Third sealing groove; 6. Positioning structure; 61. Second protrusion; 611. Avoidance groove; 7. Chamfer; 8. Engine gearbox casing; 81. Installation cavity; 82. Stop groove; 9. Sealing cover; 91. Annular sealing groove; 92. Screw; 93. O-ring seal; 10. Gear pair. Detailed implementation manners

[0036] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0037] As Figure 1 or Figure 3 shown, an embedded aeroengine gearbox lubricating nozzle includes a cavity structure 1, and a first sealing structure 2, a nozzle 3, a second sealing structure 4 and a third sealing structure 5 are sequentially arranged on the cavity structure 1.

[0038] As Figure 6 shown, an embedded aeroengine gearbox includes an engine gearbox casing 8, a sealing cover 9 and the above lubricating nozzle. An installation cavity 81 for the lubricating nozzle to be matched and embedded is opened on the engine gearbox casing 8, and the sealing cover 9 is used to seal and connect the lubricating nozzle embedded in the installation cavity 81 to the engine gearbox casing 8.

[0039] The working principle or implementation manner of the above lubricating nozzle is as follows. Refer to Figure 1 , Figure 3 and Figure 6As shown in the figure, the first sealing structure 2 is used for sealing the connection at one end of the cavity structure 1 and the installation cavity 81 of the engine gearbox casing 8. The nozzle 3 is used for multi-point lubrication of the meshing points inside the gearbox. The second sealing structure 4 is used for sealing the connection at the other end of the cavity structure 1 and the installation cavity 81 of the engine gearbox casing 8, preventing the oil on the oil passage a of the engine gearbox casing 8 from leaking into the engine gearbox, and preventing the oil inside the gearbox from being reversely introduced into the oil passage a to contaminate the relevant components. The third sealing structure 5 is used for sealing the entrance of the installation cavity 81 on the engine gearbox casing 8 for embedding the lubrication nozzle. A positioning structure 6 is also provided on the cavity structure 1, and the positioning structure 6 is used for guiding the embedding direction when the lubrication nozzle is embedded into the engine gearbox casing 8 and stopping the lubrication nozzle after installation.

[0040] According to the above working principle, the present invention also provides some preferred embodiment structures, such as Figure 3 As shown in the figure, the first sealing structure 2 includes a first sealing shaft 21 and a first shoulder 22. The first shoulder 22 is connected to one end of the first sealing shaft 21 close to the nozzle 3. A first sealing groove 211 is formed at the position of the first sealing shaft 21 close to the first shoulder 22. Refer to Figure 3 and Figure 6 As shown in the figure, by connecting a sealing ring on the first sealing groove 211, it is used to form a seal between the first sealing shaft 21 and the installation cavity 81.

[0041] Such as Figure 3 As shown in the figure, the second sealing structure 4 includes a second sealing shaft 41 and a second shoulder 42. The second shoulder 42 is connected to one end of the second sealing shaft 41 far from the nozzle 3. A second sealing groove 411 is formed at the position of the second sealing shaft 41 close to the second shoulder 42. Refer to Figure 3 and Figure 6 As shown in the figure, by connecting a sealing ring on the second sealing groove 411, it is used to form a seal between the second sealing shaft 41 and the installation cavity 81.

[0042] The sealing rings jointly use axial and radial sealing methods, that is, the first shoulder 22 and the second shoulder 42 also compress the sealing rings axially. Compared with the full use of radial compression method, it can prevent the lubricating oil from leaking to the outside of the engine gearbox casing 8. At the same time, while ensuring reliable sealing, the resistance of installation and disassembly is significantly reduced.

[0043] Such as Figure 3 As shown in the figure, the third sealing structure 5 includes a third sealing shaft 51. The third sealing shaft 51 is connected to the cavity structure 1 far from the second sealing structure 4. The third sealing shaft 51 is used to match the end of the installation cavity 81. A third sealing groove 511 is provided on the third sealing shaft 51. Refer to Figure 3 and Figure 6As shown, by connecting a sealing ring to the third sealing groove 511, it is used to form a seal between the third sealing shaft 51 and the installation cavity 81. This can ensure that the lubricating oil flows reliably through the inner cavity main flow path and the branch oil through holes of the cavity structure 1 without leakage.

[0044] As Figure 3 shown, a threaded hole 12 is provided at one end of the cavity structure 1 away from the first sealing structure 2, which is used to pull out and unload the embedded aero-engine gearbox lubricating nozzle during installation. During disassembly, the nozzle can be conveniently pulled out by using the threaded hole 12 on the nozzle in cooperation with a bolt.

[0045] Refer to Figure 3 and Figure 6 shown, the lubricating nozzle is installed in the engine gearbox casing 8. The oil path a is the main lubricating oil supply path of the engine gearbox casing 8. The lubricating oil enters the inner cavity main flow path of the cavity structure 1 through the oil path a. Part of it enters the oil path b through the branch oil through hole 11 for subsequent oil supply to other nozzles, and part of it enters the oil path c in the sealing cover 9 through the threaded hole 12 for subsequent oil supply to other nozzles. When the lubricating oil flows through the inner cavity main flow path of the cavity structure 1, under the action of pressure, it is sprayed onto the predetermined area through the oil injection holes 311 on the nozzle 3.

[0046] As Figure 1 shown, the positioning structure 6 includes a second protrusion 61. The second protrusion 61 is connected to one end of the cavity structure 1 away from the first sealing structure 2. Preferably, the second protrusion 61 can be provided on the third sealing structure 5. Refer to Figure 1 and Figure 8 shown, by only opening a stop groove 82 matching the second protrusion 61 on the installation cavity 81 of the engine gearbox casing 8, it can be used to position the aero-engine gearbox lubricating nozzle on the engine gearbox casing 8.

[0047] As Figure 6 shown, a branch oil through hole 11 is provided on the cavity structure 1 between the second sealing structure 4 and the third sealing structure 5. The branch oil through hole 11 is used to connect to a branch oil path, such as the oil path b, for oil supply to other nozzles in the engine. The branch oil path can also be provided at the front end of the main oil path in the cavity of the cavity structure 1, such as the oil path d, which belongs to an improvement of the engine gearbox casing 8 and can be reasonably added according to the lubrication point requirements and will not be elaborated here one by one.

[0048] Refer to Figure 6 and Figure 9 shown, an annular sealing groove 91 is provided on the sealing cover 9. The annular sealing groove 91 can form an end seal with the cavity structure 1 through a sealing ring. Refer to Figure 3 、 Figure 6 and Figure 9As shown, the sealing ring is pressed tightly between the annular sealing groove 91 and the lubricating nozzle, ensuring that the lubricating oil reliably flows into the oil passage c in the sealing cover 9 from the threaded hole 12 on the nozzle without leakage.

[0049] For the above-mentioned sealing ring, the sealing ring with a suitable structure can be reasonably selected according to the shape of the groove and the size of the sealing position space. Generally, a common O-ring 93 as shown can be used, which is convenient for installation and adaptation. Figure 8 As shown, the O-ring 93 is used, which is convenient for installation and adaptation.

[0050] Such as Figure 3 As shown, the nozzle 3 includes a first protrusion 31 connected to the cavity structure 1, and a plurality of oil injection holes 311 communicating with the cavity structure 1 are provided on the first protrusion 31.

[0051] Chamfers 7 are provided on both the first sealing structure 2 and the second sealing structure 4 to facilitate their insertion into the installation cavity. Refer to Figure 3 and Figure 6 As shown, since there are many spray points, the lubricating nozzle is relatively long, the installation cavity 81 is relatively deep and is a stepped hole. For the convenience of installation, the chamfer 7 or some other guiding structures such as a guiding shaft can guide the lubricating nozzle to be smoothly inserted into the installation cavity 81.

[0052] Such as Figure 7 As shown, the lubricating oil ejected from the oil injection holes 311 is sprayed near the meshing point of the gear pair 10. In order to ensure that the lubricating oil can be sprayed in a concentrated beam towards the predetermined area, it is necessary to ensure that the oil injection hole 311 of the lubricating oil has a certain length-diameter ratio (oil injection hole length / oil injection hole diameter). For weight reduction, the lubricating nozzle is generally a thin-walled part. In order to ensure the above length-diameter ratio, the first protrusion 31 is designed in the area where the oil injection hole 311 is located on the lubricating nozzle.

[0053] When it is necessary to spray oil near the gear meshing point within a certain width range, rows of oil injection holes 311 as shown can be designed, and the range of the first protrusion 31 is also increased adaptively. In order to ensure the fixed position of the spray point, it is necessary to prevent the lubricating nozzle from rotating circumferentially and moving axially during operation. Refer to Figure 3 As shown, the axial limit is achieved by the first shoulder 22, the second shoulder 42 and the sealing cover 9, and the circumferential limit is achieved by the second protrusion 61. When assembled, the second protrusion 61 is stuck in the stop groove 82 on the engine gearbox casing 8, so that the lubricating nozzle will not rotate circumferentially during operation. The above structure enables the nozzle to be reliably positioned without being fastened by screws. Figure 3 and Figure 6 and Figure 8 As shown, in order to ensure that the lubricating nozzle is assembled in place, it is necessary to note that the second protrusion 61 and the stop groove 82 should not interfere with each other. As shown in

[0054] Refer to Figure 8 As shown, in order to ensure that the lubricating nozzle is assembled in place, it is necessary to note that the second protrusion 61 and the stop groove 82 should not interfere with each other. Such as Figure 2As shown, an avoidance groove 611 is provided at the connection between the second protrusion 61 and the cavity structure 1. To prevent interference between the side of the stop protrusion of the nozzle and the engine casing, chamfers need to be made at corresponding positions on the engine gearbox casing 8.

[0055] As Figure 8 shown, the sealing cover 9 is connected to the engine gearbox casing 8 by screws 92. The sealing cover 9 is a cast part with an integrated additional nozzle. It has an internal oil passage c. The cast oil passage on the sealing cover 9 provides lubricating oil for other nozzles on the one hand and pressure oil for hydraulic actuating components on the other hand. At the same time, the sealing cover 9 and other parts together form a pressurized hydraulic chamber. Since the structure of the sealing cover 9 itself is not the point to be protected by the present invention, no detailed introduction is given here.

[0056] It should be noted that the terms "first", "second", etc. in this application are used to distinguish similar objects and do not necessarily have to be used to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so as to implement the embodiments of the present application described herein. In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings.

[0057] In the description of this specification, the description with reference to terms such as "an embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0058] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed.

Claims

1. An embedded lubricating nozzle for an aero-engine gearbox, characterized in that, it includes a cavity structure (1), on which a first sealing structure (2), a nozzle (3), a second sealing structure (4) and a third sealing structure (5) are successively arranged, and a positioning structure (6) is also arranged on the cavity structure (1); The nozzle (3) includes a first protrusion (31) connected to the cavity structure (1), and a plurality of oil injection holes (311) communicating with the cavity structure (1) are formed on the first protrusion (31); The first sealing structure (2) includes a first sealing shaft (21) and a first shoulder (22), the first shoulder (22) is connected to one end of the first sealing shaft (21) close to the nozzle (3), and a first sealing groove (211) is formed at a position of the first sealing shaft (21) close to the first shoulder (22); The second sealing structure (4) includes a second sealing shaft (41) and a second shoulder (42), the second shoulder (42) is connected to one end of the second sealing shaft (41) far from the nozzle (3), and a second sealing groove (411) is formed at a position of the second sealing shaft (41) close to the second shoulder (42); The third sealing structure (5) includes a third sealing shaft (51), the third sealing shaft (51) is connected to the cavity structure (1) far from the second sealing structure (4), and a third sealing groove (511) is arranged on the third sealing shaft (51); The positioning structure (6) includes a second protrusion (61), and the second protrusion (61) is connected to one end of the cavity structure (1) far from the first sealing structure (2).

2. The embedded lubricating nozzle for an aero-engine gearbox according to claim 1, characterized in that, a bypass oil hole (11) is arranged on the cavity structure (1) between the second sealing structure (4) and the third sealing structure (5).

3. The embedded lubricating nozzle for an aero-engine gearbox according to claim 1, characterized in that, a threaded hole (12) is arranged at one end of the cavity structure (1) far from the first sealing structure (2).

4. An embedded aero-engine gearbox, characterized in that, it includes an engine gearbox casing (8), a sealing cover (9) and the lubricating nozzle according to any one of claims 1-3. An installation cavity (81) for the matching and embedding of the lubricating nozzle is formed on the engine gearbox casing (8), and the sealing cover (9) is used to seal and connect the lubricating nozzle embedded in the installation cavity (81) to the engine gearbox casing (8).

5. The embedded aero-engine gearbox according to claim 4, characterized in that, an annular sealing groove (91) is formed on the sealing cover (9), and the annular sealing groove (91) can form an end seal with the cavity structure (1) through a sealing ring.

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