An aeroengine accessory gearbox cooling and lubrication structure and method

Abstract

The application provides an aero-engine accessory case cooling and lubricating structure and method, which comprises a case provided with a case oil passage hole and an oil collecting pool, the oil collecting pool is used for collecting lubricating oil, and the lubricating oil in the oil collecting pool can enter the case oil passage hole; an oil guiding device is assembled on the case, the oil guiding device is provided with an oil guiding oil passage hole, one end of the oil guiding oil passage hole is connected with the case oil passage hole, and the other end of the oil guiding oil passage hole is connected with one end of a central hole of a gear shaft; wherein the gear shaft contains a spline; an oil baffle is assembled at the other end of the central hole of the gear shaft, and a plurality of axial and radial oil passages are arranged at the edge position of the oil baffle; the aero-engine accessory case cooling and lubricating structure and method provided by the application can realize the lubrication of bearings and splines under the condition of no forced lubrication, and ensure the normal work of bearings and splines.

Description

Technical Field

[0001] This application belongs to the field of aircraft engine accessory housing technology, and particularly relates to a cooling and lubrication structure and method for an aircraft engine accessory housing. Background Technology

[0002] In the accessory transmission housing of an aero-engine, the bearings are mainly used to bear axial and radial loads. The cooling and lubrication effect directly affects the bearing's load-bearing capacity and may even lead to bearing failure. Splines are commonly used to connect gear shafts and accessories, and gear discs and shafts. The micro-movements between spline pairs generate heat. If the heat is not dissipated in time, it will cause abnormal wear of the splines.

[0003] Currently, aircraft engines typically use jet propulsion to force-cool and lubricate splines and bearings. However, some engines are limited by their structure and size and cannot be equipped with nozzles for forced lubrication.

[0004] Therefore, there is a need to provide a cooling and lubrication structure and method for aircraft engine accessory casings under non-forced lubrication conditions. Summary of the Invention

[0005] The purpose of this invention is to provide a structure and method for lubricating bearings and splines in the accessory housing of an aero-engine, so as to achieve lubrication of the bearings and splines without forced lubrication and ensure the normal operation of the bearings and splines.

[0006] In a first aspect, this application provides a cooling and lubrication structure for an aircraft engine accessory casing, comprising: The casing is provided with a casing oil passage and an oil collection tank. The oil collection tank is used to collect lubricating oil, and the lubricating oil in the oil collection tank can enter the casing oil passage. An oil guiding device is mounted on the casing. The oil guiding device is provided with an oil guiding passage hole. One end of the oil guiding passage hole is connected to the oil passage hole of the casing, and the other end of the oil guiding passage hole is connected to one end of the center hole of the gear shaft. The gear shaft contains a spline. An oil baffle is fitted to the other end of the central hole of the gear shaft, and the oil baffle has several axial and radial oil passages at its edge. The lubricating oil in the oil collection pool enters the central hole of the gear shaft through the oil passage hole of the casing and the oil guide hole. After the lubricating oil reaches the oil baffle, it lubricates the bearing ring under the radial oil passage of the oil baffle and the spline along the axial oil passage.

[0007] Preferably, the oil collection pool is located near the oil passage hole of the casing.

[0008] Preferably, the oil guiding device is assembled on the casing in an interference fit.

[0009] Preferably, one end of the oil guide hole is connected to the casing oil passage hole by a locating pin, and the other end of the oil guide hole is coaxial with the center hole of the gear shaft.

[0010] Preferably, the oil guide holes are perpendicularly intersecting holes.

[0011] Preferably, the oil guide hole is an L-shaped hole.

[0012] Secondly, this application also provides a method for cooling and lubricating an aircraft engine accessory housing, the method being applied to the aircraft engine accessory housing cooling and lubrication structure as described above, the method comprising: When the engine is running, lubricating oil is collected in the oil sump; The lubricating oil in the oil collection pool enters the center hole of the gear shaft through the oil passage of the casing and the oil guide hole, reaching the oil baffle. Under the action of gravity, it reaches the spline, and under the action of centrifugal force, it reaches the bearing, thus achieving lubrication of the spline and bearing.

[0013] Preferably, the inner ring of the bearing is split in half, with oil supplied from below the ring.

[0014] The beneficial technical effects of this application are as follows: This invention provides a cooling and lubrication structure and method for an aero-engine accessory housing. This invention eliminates the need for separate oil lines and nozzles for forced lubrication, and can achieve lubrication of splines and bearings under the action of centrifugal force and gravity, greatly simplifying the accessory housing structure and reducing the weight of the accessory housing. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the cooling and lubrication structure of the aero-engine accessory casing of the present invention; Figure 2 This is a schematic diagram of the oil-blocking cup structure provided by the present invention; Figure 3 A schematic diagram of the oil-blocking bowl provided by the present invention from another perspective; Explanation of reference numerals in the attached drawings: 1—casing; 2—oil guiding device; 3—gear shaft; 4—oil baffle; 5—bearing; 6—casing oil collection basin; 7—spline; 8—lubricating oil track; 9—radial oil passage; 10—axial oil passage. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0019] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0020] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0021] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] The following is a description of the embodiments and appendices. Figure 1 -Appendix Figure 3 The present invention will be described in further detail below, but the embodiments of the present invention are not limited thereto.

[0023] The present invention provides a structure for lubrication of bearings and splines in an aero-engine accessory casing, comprising a casing, an oil guide device, a gear shaft (including splines), and an oil baffle.

[0024] The gearbox features oil passages integrated into the casing via casting or machining. An oil collection basin is located near these passages to collect lubricating oil and guide it into the passages. An oil guide device is interference-fitted to the casing. This device has perpendicularly intersecting oil passages, with a locating pin ensuring one end connects to the casing's oil passage and the other end is coaxial with the gear shaft's center hole. Lubricating oil enters the gear shaft's center hole through the casing's oil passage and the perpendicularly intersecting oil passages of the oil guide device. An oil baffle is fitted into the gear shaft's center hole. The baffle has several axial and radial oil passages along its edge. Upon reaching the baffle, the oil lubricates the bearing rings along the radial oil passages and the splines along the axial oil passages.

[0025] In other embodiments of this application, the present invention provides a cooling and lubrication method for an aircraft engine accessory housing, comprising: Step 1: The structure and method of gravity lubrication of the bearings and splines of the aircraft engine accessory casing include the casing, oil guide device, gear shaft (including splines), and oil baffle. Step 2: The oil collection pool and oil passages are set on the casing. Preferably, the oil guide device is provided with perpendicularly intersecting oil passages, and the oil baffle is provided with several axial and radial oil passages.

[0026] Step 3: Determine the dimensions of the oil passage inlet, oil guide device, and oil baffle bowl based on the actual lubrication requirements of the splines and bearings; Step 4: Install the oil baffle bowl inside the gear shaft, install the oil guide device inside the bearing hole of the gearbox, and install the positioning pin on the oil guide device to ensure that the oil passage of the oil guide device is aligned with the oil passage of the gearbox.

[0027] Step 5: When the engine is running, a portion of lubricating oil will be collected in the oil sump of the casing. The lubricating oil in the oil sump passes through the oil passage of the casing, the oil passage of the oil guide device, and the oil passage of the oil baffle. Under the action of centrifugal force and gravity, the oil achieves spline lubrication and bearing (preferably, the inner ring of the bearing adopts a split form) under-ring lubrication.

[0028] This invention provides a cooling and lubrication structure and method for an aero-engine accessory housing. This invention eliminates the need for separate oil lines and nozzles for forced lubrication, and can achieve lubrication of splines and bearings under the action of centrifugal force and gravity, greatly simplifying the accessory housing structure and reducing the weight of the accessory housing.

[0029] Reference Figure 1When the engine is running, a certain amount of lubricating oil is collected in the oil sump of the casing. It first enters the vertically intersecting oil passage of the oil guide device, then enters the central hole of the gear shaft, and reaches the oil baffle. Under the action of gravity and centrifugal force, the lubricating oil lubricates the splines and bearings. See the lubricating oil lubrication trajectory for details.

[0030] Figure 2 and Figure 3 This is a schematic diagram of the oil baffle structure provided by the present invention. The radial oil passage is used for bearing lubrication, and the axial oil passage is used for spline lubrication.

[0031] In other embodiments of this application, the present invention provides a cooling and lubrication method for an aircraft engine accessory housing, comprising: Step 1: The structure and method of gravity lubrication of the bearings and splines of the aircraft engine accessory casing include the casing, oil guide device, gear shaft (including splines), and oil baffle. Step 2: The oil collection pool and oil passages are set on the casing. Preferably, the oil guide device is provided with vertically intersecting oil passages. One end of the vertically intersecting oil passages of the oil guide device is the same as the oil pool, and the other end is the same as the inner hole of the gear shaft. Several axial and radial oil passages are set on the oil baffle.

[0032] Step 3: Determine the dimensions of the oil passage inlet, oil guide device, and oil baffle bowl based on the actual lubrication requirements of the splines and bearings; Step 4: Install the oil baffle bowl inside the gear shaft, install the oil guide device inside the bearing hole of the gearbox, and install the positioning pin on the oil guide device to ensure that the oil passage of the oil guide device is aligned with the oil passage of the gearbox.

[0033] Step 5: When the engine is running, a portion of lubricating oil will be collected in the oil sump of the casing. The lubricating oil in the oil sump passes through the oil passage of the casing, the oil passage of the oil guide device, and the oil passage of the oil baffle. Under the action of centrifugal force and gravity, the oil achieves spline lubrication and bearing (preferably, the inner ring of the bearing adopts a split form) under-ring lubrication.

[0034] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A cooling and lubrication structure for an aircraft engine accessory housing, characterized in that, include: The casing is provided with a casing oil passage and an oil collection tank. The oil collection tank is used to collect lubricating oil, and the lubricating oil in the oil collection tank can enter the casing oil passage. An oil guiding device is mounted on the casing. The oil guiding device is provided with an oil guiding passage hole. One end of the oil guiding passage hole is connected to the oil passage hole of the casing, and the other end of the oil guiding passage hole is connected to one end of the center hole of the gear shaft. The gear shaft contains a spline. An oil baffle is fitted to the other end of the central hole of the gear shaft, and the oil baffle has several axial and radial oil passages at its edge. The lubricating oil in the oil collection pool enters the central hole of the gear shaft through the oil passage hole of the casing and the oil guide hole. After the lubricating oil reaches the oil baffle, it lubricates the bearing ring under the radial oil passage of the oil baffle and the spline along the axial oil passage.

2. The cooling and lubrication structure for an aero-engine accessory housing according to claim 1, characterized in that, The oil collection pool is located near the oil passage of the casing.

3. The cooling and lubrication structure for an aero-engine accessory housing according to claim 1, characterized in that, The oil guiding device is fitted onto the casing in an interference fit.

4. The cooling and lubrication structure for an aero-engine accessory housing according to claim 1, characterized in that, One end of the oil guide hole is connected to the casing oil passage hole by a positioning pin, and the other end of the oil guide hole is coaxial with the center hole of the gear shaft.

5. The cooling and lubrication structure for an aero-engine accessory housing according to claim 4, characterized in that, The oil guide holes are perpendicularly intersecting holes.

6. The cooling and lubrication structure for an aero-engine accessory housing according to claim 5, characterized in that, The oil guide hole is L-shaped.

7. A method for cooling and lubricating an aircraft engine accessory housing, characterized in that, The method is applied to the cooling and lubrication structure of the aircraft engine accessory casing as described in any one of claims 1-6, and the method includes: When the engine is running, lubricating oil is collected in the oil sump; The lubricating oil in the oil collection pool enters the center hole of the gear shaft through the oil passage of the casing and the oil guide hole, reaching the oil baffle. Under the action of gravity, it reaches the spline, and under the action of centrifugal force, it reaches the bearing, thus achieving lubrication of the spline and bearing.

8. The method according to claim 7, characterized in that, The bearing inner ring is split in half, with oil supplied from below the ring.

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