润滑科技信息平台

专利摘要

提供了一种减速齿轮箱(38),其包括设置在壳体(44)中的行星齿轮装置(42)和润滑处理系统(96)。行星齿轮装置(42)包括太阳齿轮(46)、行星齿轮组件(48)以及独立的前后齿圈(50A、50B)。每个行星齿轮组件(48)具有分别设置在主齿轮(58)的相对侧并随其旋转的前侧齿轮和后侧齿轮(60、62)。主齿轮(58)具有主齿轮节圆直径(PDMG),并且前侧齿轮和后侧齿轮(60、62)具有侧齿轮节圆直径(PDLG)。前齿圈(50A)与前侧齿轮(60)啮合。后齿圈(50B)与后侧向齿轮(62)啮合。行星齿轮组件(48)与输出端(40)连通。润滑处理系统(96)包括前齿圈挡板(98A)和后齿圈挡板(98B)。 ......

基本信息

专利类型:
发明专利
申请/专利号:
EP2024173939
申请日期:
2024-05-02
专利申请人:
分类号:
["F02C3/107","F02C7/36","F16H57/04"]
发明/设计人:
DESJARDINS, MICHEL ， TURCOTTE, HERVE
权利要求: 1. A reduction gearbox, comprising: a casing (44); a planetary gear arrangement (42) disposed in the casing (44), the planetary gear arrangement (42) having: a sun gear (46); a plurality of planet gear assemblies (48), each planet gear assembly (48) having a main gear (58) meshed with the sun gear (46), a fore lateral gear (60) and an aft lateral gear (62) disposed on opposite sides of the main gear (58) and rotating therewith, the main gear (58) having a main gear pitch diameter (PDMG) and the fore and aft lateral gears (60, 62) having a lateral gear pitch diameter (PDLG); and a fore ring gear (50A) meshed with the fore lateral gears (60); and an aft ring gear (50B) meshed with the aft lateral gears (62), wherein the aft ring gear (50B) is independent of the fore ring gear (50A), wherein the plurality of planet gear assemblies (48) are in communication with an output (40); and a lubrication handling system (96) that includes a first set of baffles (98) including a fore ring gear baffle (98A) disposed on a fore side of the planetary gear arrangement (42) proximate the fore ring gear (50A), and an aft ring gear baffle (98B) disposed on an aft side of the planetary gear arrangement (42) proximate the aft ring gear (50B).2. A gas turbine engine, comprising: a compressor (24B); a combustor (26); and a turbine (28B) in communication with the compressor (24B) and the reduction gearbox (38) of any preceding claim.3. The reduction gear box or gas turbine engine of claim 1 or 2, wherein the first set of baffles (98) are in communication with one or more passages (114, 116) extending to a scavenge cavity (112).4. The reduction gear box or gas turbine engine of claim 3, wherein the fore ring gear baffle (98A) includes a plurality of first apertures (104) disposed so that lubrication oil passes through the plurality of first apertures (104) prior to entering the one or more passages (114, 116) extending to the scavenge cavity (112), and the aft ring gear baffle (98B) includes a plurality of second apertures (104) disposed so that lubrication oil passes through the plurality of second apertures (104) prior to entering the one or more passages (114, 116) extending to the scavenge cavity (112).5. The reduction gear box or gas turbine engine of claim 4, wherein the plurality of first apertures (104) are disposed around a circumference of the fore ring gear baffle (98A), and the plurality of second apertures (104) are disposed around a circumference of the aft ring gear baffle (98B).6. The reduction gear box or gas turbine engine of claim 4 or 5, wherein the fore ring gear baffle (98A) includes a fore ring gear baffle first segment (102A) and a fore ring gear baffle second segment (106A) connected to the fore ring gear baffle first segment (102A), the fore ring gear baffle first segment (102A) extending axially between the casing (44) and the fore ring gear (50A), and the fore ring gear baffle second segment (106A) extending radially inward, wherein the plurality of first apertures (104) are disposed in the fore ring gear baffle first segment (102A); and the aft ring gear baffle (98B) includes an aft ring gear baffle first segment (102B) and an aft ring gear baffle second segment (106B) connected to the aft ring gear baffle first segment (102B), the aft ring gear baffle first segment (102B) extending axially between the casing (44) and the aft ring gear (50B), and the aft ring gear baffle second segment (106B) extending radially inward, wherein the plurality of second apertures (104) are disposed in the aft ring gear baffle first segment (102B).7. The reduction gear box or gas turbine engine of claim 6, wherein the fore ring gear baffle first segment (102A) extends axially between the casing (44) and the fore ring gear (50A), and the aft ring gear baffle first segment (102B) extends axially between the casing (44) and the aft ring gear (50B),8. The reduction gear box or gas turbine engine of claim 6 or 7, wherein the plurality of first apertures (104) are disposed around a circumference of the fore ring gear baffle first segment (102A), and the plurality of second apertures (104) are disposed around a circumference of the aft ring gear baffle first segment (102B).9. The reduction gear box or gas turbine engine of any of claims 6 to 8, wherein the fore ring gear baffle first segment (102A) is configured to constrain axial movement of the fore ring gear (50A), and the aft ring gear baffle first segment (102B) is configured to constrain axial movement of the aft ring gear (50B).10. The reduction gear box or gas turbine engine of any of claims 3 to 9, wherein the fore ring gear baffle (98A) disposed on the fore side of the planetary gear arrangement (42) is in communication with a fore first cavity (110A) and at least one of the one or more passages (114, 116) provides fluid communication between the fore first cavity (110A) and the scavenge cavity (112), and the aft ring gear baffle (98B) disposed on the aft side of the planetary gear arrangement (42) is in communication with an aft first cavity (110B) and at least one of the one or more passages (114, 116) provides fluid communication between the aft first cavity (110B) and the scavenge cavity (112).11. The reduction gear box or gas turbine engine of any preceding claim, wherein the lubrication handling system (96) further includes a second set of baffles (100) including a fore main gear baffle (100A) disposed on a fore side of the main gears (58) of the planet gear assemblies (48), and an aft main gear baffle (100B) disposed on an aft side of the main gears (58) of the planet gear assemblies (48).12. The reduction gear box or gas turbine engine of claim 11, wherein the fore main gear baffle (100A) is configured to direct lubrication oil to a fore second cavity (108A) and at least one of the one or more passages (114, 116) provides fluid communication between the fore second cavity (108A) and the scavenge cavity (112), and the aft main gear baffle (100B) is configured to direct lubrication oil to an aft second cavity (108B) and at least one of the one or more passages (114, 116) provides fluid communication between the aft second cavity (108B) and the scavenge cavity (112).