CN112343996A - Aeroengine accessory case idler structure - Google Patents

Aeroengine accessory case idler structure Download PDF

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Publication number
CN112343996A
CN112343996A CN202011224020.9A CN202011224020A CN112343996A CN 112343996 A CN112343996 A CN 112343996A CN 202011224020 A CN202011224020 A CN 202011224020A CN 112343996 A CN112343996 A CN 112343996A
Authority
CN
China
Prior art keywords
idler
wheel
bearing
shaft
accessory case
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202011224020.9A
Other languages
Chinese (zh)
Inventor
朱博强
李博
吴双峰
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Shenyang Engine Research Institute
Original Assignee
AECC Shenyang Engine Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Engine Research Institute filed Critical AECC Shenyang Engine Research Institute
Priority to CN202011224020.9A priority Critical patent/CN112343996A/en
Publication of CN112343996A publication Critical patent/CN112343996A/en
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/021—Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/023—Mounting or installation of gears or shafts in the gearboxes, e.g. methods or means for assembly
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/03—Gearboxes; Mounting gearing therein characterised by means for reinforcing gearboxes, e.g. ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/038—Gearboxes for accommodating bevel gears
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H2057/02039—Gearboxes for particular applications
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H2057/02086—Measures for reducing size of gearbox, e.g. for creating a more compact transmission casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H2057/02091—Measures for reducing weight of gearbox
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/021—Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
    • F16H2057/0216—Intermediate shaft supports, e.g. by using a partition wall

Abstract

The application provides an aeroengine annex machine casket idle structure, the idle structure includes: one end of the idler shaft is fixed to the front shell of the accessory case through a pressing plate, and the other end of the idler shaft is fixed to the rear shell of the accessory case; the bearing is sleeved on the idler shaft; and the gear ring is arranged on the bearing and is used for transmitting the transmission between the first heavy-duty wheel and the second heavy-duty wheel. The idler wheel structure provided by the application reduces the dynamic unbalance amount of the gear shaft and the gyro moment by enabling the idler wheel shaft not to rotate; the idler shaft is rigidly connected with the accessory casing, so that the rigidity of the casing is increased, and the deformation of the casing during heavy load is reduced; the idler shaft is of a single-bearing structure, so that the length of the gear shaft can be shortened, the weight is reduced, and the space is saved; the bearing with larger diameter can be used under the original space condition, and the service life reliability of the bearing is improved.

Description

Aeroengine accessory case idler structure
Technical Field
The application belongs to the technical field of aero-engine transmission, and particularly relates to an idler wheel structure of an aero-engine accessory casing.
Background
As shown in fig. 1, on the heavy-duty side of an aircraft engine accessory case, limited by the center distance of the accessories mounted on the accessory case, an idler pulley 20 is often provided between a heavy-duty wheel 10 and a heavy-duty wheel 30 to extend the drive chain, and the idler pulley 20 is fixed to a front case 40 and a rear case 50 of the accessory case through bearings at both ends.
However, due to the length of the transmission chain, bearing play and machining errors tend to cause gear tooth flank unbalance wear between bull wheel 10 and idler wheel 20 or between bull wheel 30 and idler wheel 20, and due to insufficient stiffness of the attachment case housing, the housing deformation during heavy loading exacerbates gear unbalance wear.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine accessory case idler structure that addresses or mitigates at least one of the problems of the background art.
The technical scheme of the application is as follows: an aircraft engine accessory case idler structure, the idler structure comprising:
one end of the idler shaft is fixed to the front shell of the accessory case through a pressing plate, and the other end of the idler shaft is fixed to the rear shell of the accessory case;
the bearing is sleeved on the idler shaft; and
and the gear ring is arranged on the bearing and is used for transmitting transmission between the first heavy-duty wheel and the second heavy-duty wheel.
In an embodiment of the application, the bearing is secured by a collar.
In an embodiment of the present application, a first sealing ring is disposed between the pressure plate and the front housing; and a second sealing ring is arranged between the idler shaft and the rear shell.
In a second aspect, the present application provides the following technical solutions: an aircraft engine accessory case idler structure, the idler structure comprising:
one end of the idler shaft is inserted into the groove of the front shell, and the other end of the idler shaft is fixed to the rear shell of the accessory casing;
the bearing is sleeved on the idler shaft; and
and the gear ring is arranged on the bearing and is used for transmitting transmission between the first heavy-duty wheel and the second heavy-duty wheel.
In an embodiment of the application, the bearing is secured by a collar.
In an embodiment of the present application, a first sealing ring is disposed between the pressure plate and the front housing; and a second sealing ring is arranged between the idler shaft and the rear shell.
In a third aspect, the technical solution provided by the present application is: an aircraft engine transmission structure, the transmission structure comprising:
a first weight wheel;
a second reload wheel; and
an idler wheel disposed between the first and second bull wheels, the idler wheel having an idler wheel structure as described in any of the first to third aspects.
In a third aspect, the technical solution provided by the present application is: an aircraft engine transmission structure, the transmission structure comprising:
a first weight wheel;
a second reload wheel; and
and an idler wheel disposed between the first and second reloading wheels, wherein the idler wheel is configured as described in any one of the second aspects.
The idler wheel structure provided by the application reduces the dynamic unbalance amount of the gear shaft and the gyro moment by enabling the idler wheel shaft not to rotate; the idler shaft is rigidly connected with the accessory casing, so that the rigidity of the casing is increased, and the deformation of the casing during heavy load is reduced; the idler shaft is of a single-bearing structure, so that the length of the gear shaft can be shortened, the weight is reduced, and the space is saved; the bearing with larger diameter can be used under the original space condition, and the service life reliability of the bearing is improved.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic diagram of a transmission structure in an accessory case in the prior art.
FIG. 2 is a schematic view of an exemplary embodiment of an idler gear for an aircraft engine accessory case.
FIG. 3 is a schematic view of an aircraft engine accessory case idler wheel configuration according to another embodiment of the present application.
Fig. 4 is a schematic view of an internal transmission structure of an accessory case according to the first embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to overcome the problems that the rigidity of a casing shell at an idler wheel of an accessory casing in the prior art is insufficient and the idler wheel is easy to generate unbalance loading, the application provides an idler wheel structure.
As shown in fig. 2, the present application provides an embodiment of an aero-engine accessory case idler structure comprising: idler shaft 21A, pressure plate 22A, bearing 25A and gear ring 26A. The idler shaft 21A and the pressing plate 22A may form an idler body structure, the upper end of the idler shaft 21A is inserted into the pressing plate 22A to realize relative positioning, the pressing plate 22A is connected to the front casing 23A of the accessory casing through bolts, and the lower end of the idler shaft 21A is directly fixed to the rear casing 24A of the accessory casing through bolts. A bearing 25A is mounted on the idler shaft and a gear ring 26A is mounted on the bearing 25A. Carried by the fixed idler body structure, the transfer of rotation between the first and second road wheels occurs through the gear ring 26.
In this embodiment, the bearing 25A may be axially positioned by a collar 29A.
In the present embodiment, a first seal 27A may be provided between the pressure plate 22A and the front housing 23A, and a second seal 28A may be provided between the idler shaft 21A and the rear housing 24A.
As shown in fig. 3, another embodiment of an aero-engine accessory case idler structure provided herein comprises: idler shaft 21A, bearing 25A, and gear ring 26A. The idler shaft 21A itself may constitute an idler body structure, the upper end of the idler shaft 21B is inserted into the groove 22B of the front housing 23B to realize relative positioning, and the lower end of the idler shaft 21B is directly fixed on the rear housing 24B of the accessory casing through bolts. Bearing 25B is mounted on idler shaft 21B, and gear ring 26BB is mounted on bearing 25B. Carried by the fixed idler body structure, the transfer of rotation between the first and second bull wheels occurs through the gear ring 26B.
In this embodiment, the bearing 25B may be axially positioned by a collar 29B.
In the present embodiment, a first seal 27B may be provided between the pressure plate 22B and the front housing 23B, and a second seal 28B may be provided between the idler shaft 21B and the rear housing 24B.
Finally, as shown in fig. 4, the present application also provides an aircraft engine transmission structure, which includes a first heavy-duty wheel, a second heavy-duty wheel and an idler wheel arranged between the first heavy-duty wheel and the second heavy-duty wheel, wherein the idler wheel adopts the idler wheel structure in the first or second embodiment. Fig. 3 shows an idler structure 20A in a first embodiment.
The idler structure and the transmission structure with the idler structure provided by the application have the following advantages:
1) the idler shaft does not rotate, so that the dynamic unbalance amount of the gear shaft and the gyro moment are reduced;
2) the idler shaft is rigidly connected with the accessory casing, so that the rigidity of the casing is increased, and the deformation of the casing during heavy load is reduced;
3) the idler wheel is changed into a single bearing structure, so that the length of a gear shaft can be shortened, the weight is reduced, and the space is saved; the bearing with larger diameter can be used under the original space condition, and the service life reliability of the bearing is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (8)

1. An aircraft engine accessory case idler structure, the idler structure comprising:
one end of the idler shaft is fixed to the front shell of the accessory case through a pressing plate, and the other end of the idler shaft is fixed to the rear shell of the accessory case;
the bearing is sleeved on the idler shaft; and
and the gear ring is arranged on the bearing and is used for transmitting transmission between the first heavy-duty wheel and the second heavy-duty wheel.
2. The aero engine accessory case idler structure according to claim 1 wherein said bearing is secured by a collar.
3. The aircraft engine accessory case idler gear structure according to claim 1, wherein a first seal is disposed between said pressure plate and said front housing; and a second sealing ring is arranged between the idler shaft and the rear shell.
4. An aircraft engine accessory case idler structure, the idler structure comprising:
one end of the idler shaft is inserted into the groove of the front shell, and the other end of the idler shaft is fixed to the rear shell of the accessory casing;
the bearing is sleeved on the idler shaft; and
and the gear ring is arranged on the bearing and is used for transmitting transmission between the first heavy-duty wheel and the second heavy-duty wheel.
5. The aero engine accessory case idler structure according to claim 1 wherein said bearing is secured by a collar.
6. The aircraft engine accessory case idler gear structure according to claim 1, wherein a first seal is disposed between said pressure plate and said front housing; and a second sealing ring is arranged between the idler shaft and the rear shell.
7. An aircraft engine transmission structure, characterized in that the transmission structure comprises:
a first weight wheel;
a second reload wheel; and
an idler wheel disposed between the first and second road wheels, the idler wheel having an idler wheel structure as claimed in any one of claims 1 to 3.
8. An aircraft engine transmission structure, characterized in that the transmission structure comprises:
a first weight wheel;
a second reload wheel; and
an idler wheel disposed between the first and second road wheels, the idler wheel having an idler wheel structure as claimed in any one of claims 4 to 6.
CN202011224020.9A 2020-11-05 2020-11-05 Aeroengine accessory case idler structure Pending CN112343996A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011224020.9A CN112343996A (en) 2020-11-05 2020-11-05 Aeroengine accessory case idler structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011224020.9A CN112343996A (en) 2020-11-05 2020-11-05 Aeroengine accessory case idler structure

Publications (1)

Publication Number Publication Date
CN112343996A true CN112343996A (en) 2021-02-09

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Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5031477A (en) * 1989-07-13 1991-07-16 Self-Changing Gears Limited Multiple accessory drive gearbox with alternative inputs
US20070006675A1 (en) * 2003-05-22 2007-01-11 Durgaprasad Marla Power transfer unit
US20080053257A1 (en) * 2006-08-29 2008-03-06 Snecma Device for driving the rotor of turbine engine auxiliary
CN202955203U (en) * 2012-10-11 2013-05-29 龙工(上海)机械制造有限公司 Idler device for speed changing box of loading machine
CN203868107U (en) * 2014-06-04 2014-10-08 哈尔滨博业科技开发有限责任公司 Full complement cylindrical roller idler wheel bearing of coal mining machine
CN107074355A (en) * 2014-10-20 2017-08-18 赛峰直升机发动机公司 Removable sub-assembly for restarting turboaxle motor, the framework and corresponding helicopter of the propulsion system of the multi engine helicopter provided with this sub-assembly
CN206571948U (en) * 2017-02-15 2017-10-20 徐州徐工传动科技有限公司 Big carrying idle pulley axle construction
CN109297459A (en) * 2018-12-16 2019-02-01 中国航发沈阳发动机研究所 Accessory drive gearbox spline angle error measurement method
CN110285207A (en) * 2019-06-14 2019-09-27 安徽航瑞航空动力装备有限公司 Vibration absorber suitable for aero-engine reduction gearbox

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5031477A (en) * 1989-07-13 1991-07-16 Self-Changing Gears Limited Multiple accessory drive gearbox with alternative inputs
US20070006675A1 (en) * 2003-05-22 2007-01-11 Durgaprasad Marla Power transfer unit
US20080053257A1 (en) * 2006-08-29 2008-03-06 Snecma Device for driving the rotor of turbine engine auxiliary
CN202955203U (en) * 2012-10-11 2013-05-29 龙工(上海)机械制造有限公司 Idler device for speed changing box of loading machine
CN203868107U (en) * 2014-06-04 2014-10-08 哈尔滨博业科技开发有限责任公司 Full complement cylindrical roller idler wheel bearing of coal mining machine
CN107074355A (en) * 2014-10-20 2017-08-18 赛峰直升机发动机公司 Removable sub-assembly for restarting turboaxle motor, the framework and corresponding helicopter of the propulsion system of the multi engine helicopter provided with this sub-assembly
CN206571948U (en) * 2017-02-15 2017-10-20 徐州徐工传动科技有限公司 Big carrying idle pulley axle construction
CN109297459A (en) * 2018-12-16 2019-02-01 中国航发沈阳发动机研究所 Accessory drive gearbox spline angle error measurement method
CN110285207A (en) * 2019-06-14 2019-09-27 安徽航瑞航空动力装备有限公司 Vibration absorber suitable for aero-engine reduction gearbox

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Application publication date: 20210209