CN110337532A - 包括在两个同心轴之间的轴承的飞行器发动机 - Google Patents
包括在两个同心轴之间的轴承的飞行器发动机 Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
- F16C27/06—Elastic or yielding bearings or bearing supports, for exclusively rotary movement by means of parts of rubber or like materials
- F16C27/066—Ball or roller bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/08—Restoring position
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
- F01D25/164—Flexible supports; Vibration damping means associated with the bearing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
- F16C35/04—Rigid support of bearing units; Housings, e.g. caps, covers in the case of ball or roller bearings
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
- F16C35/04—Rigid support of bearing units; Housings, e.g. caps, covers in the case of ball or roller bearings
- F16C35/06—Mounting or dismounting of ball or roller bearings; Fixing them onto shaft or in housing
- F16C35/07—Fixing them on the shaft or housing with interposition of an element
- F16C35/077—Fixing them on the shaft or housing with interposition of an element between housing and outer race ring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/50—Bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/50—Bearings
- F05D2240/54—Radial bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/60—Shafts
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2326/00—Articles relating to transporting
- F16C2326/43—Aeroplanes; Helicopters
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
Abstract
轴(7,8)间轴承(11),该轴承由支撑件(12)支撑,支撑件基本上包括实心刚性主体(13),该实心刚性主体在正常操作期间或多或少是不可变形的,但是在应力过大的情况下,例如在叶片发生故障的情况下,实心刚性主体会断裂。包括在支撑件(12)中的阻尼器(14)限制两个轴(7,8)之间的移动并且防止过度的不稳定。
Description
技术领域
本发明的客体是飞行器发动机,该飞行器发动机包括在两个同心轴之间的轴承,这两个同心轴通常为涡轮机的低压转子轴和高压转子轴。
背景技术
如果发生诸如叶片破裂,特别是可能由在发动机入口处的碎屑吸入引起的、属于低压转子的低压叶片破裂的故障,主要是如果轴轴承中的一个轴轴承的支撑件断裂并且出现轴风车般的转动的情况,则这种转子中出现的不平衡是造成显著振动和径向移动的原因。因此,显著的载荷和移动也可以通过轴间轴承传递到高压转子,与两个轴相关联的转子之间可能发生接触,并且发动机可能停机或破坏。
发明内容
本发明的主要目的是通过限制受损转子可能传递到保持完好的转子上的损坏、载荷和/或冲击并且因此通过使得至少在降级的发动机模式下可以在足够的持续时间内保持操作以减小事故风险或重力来限制出现不平衡的后果,特别是限制叶片破裂之后,保持完好的转子上出现不平衡的后果。
在一般形式下,本发明涉及一种飞行器发动机,该飞行器发动机包括沿发动机轴向方向延伸的两个同心轴、支撑轴中的第一轴的轴承、以及将轴承连接到轴中的第二轴的支撑件,其特征在于,支撑件包括机械分离器,机械分离器主要由刚性主体和阻尼器主体组成,刚性主体通过沿垂直于轴向方向的发动机径向方向的两个相对表面抵接在分别与第二轴和轴承为一体的两个抵接表面上,刚性主体能够在待在抵接表面之间传递的载荷阈值处破裂,阻尼器主体被容置在支撑件的由抵接表面界定的腔中。
该设备的主要特点是该设备在正常操作中保持支撑刚度,因此不存在导致不稳定的风险,这与传统的阻尼器支撑件不同,但是,如果发生诸如叶片破裂的事故,则轴与轴之间产生径向移动式显著分离,这将导致足以使设备破裂的不平衡。因此,高压轴的径向移动受低压轴的径向移动的影响不大,并且高压轴的操作也不会有太大恶化。这种分离器带有可能减轻受损转子的不稳定性的阻尼器。换句话说,该系统包括使相应的轴承部分分别与轴成一体的状态和使所述轴承部分之一能够相对于与所述轴承部分之一成一体的轴沿径向方向移动并且相对于所述轴受到阻尼的状态。
在可以为这种基本设计提出的改进中,会涉及以下几种改进:刚性主体由两个部件组成,每个部件在抵接表面之间界定腔,从而便于保护阻尼器主体;刚性主体由脆性材料制成,在达到破裂阈值时,脆性材料立即被破坏并释放阻尼器主体;合适的脆性材料是陶瓷,陶瓷可以是多孔的;可以对脆性材料施加预应力;阻尼器主体可以是弹性体的或由填充有流体的袋组成。
附图说明
将结合附图对本发明进行描述,附图描述了本发明的一些可能的实施例,而不排斥其他实施例:
-图1为根据本发明的发动机的整体视图;
-图2示出了典型设备;
-图3示出了发生故障时的同一设备和发动机操作;
-图4、图5、图6和图7是本发明的刚性主体的四个替代性实施例。
具体实施方式
参考图1。
传统类型的飞行器涡轮机沿气体流动流1和轴向方向X依次包括:低压压缩机2、高压压缩机3、燃烧室4、高压涡轮5和低压涡轮6,压缩机和涡轮由沿流1交替的固定叶片级和可移动叶片级组成。可移动叶片依赖于转子,转子特别地包括低压轴7和高压轴8,低压压缩机2的可移动叶片和低压涡轮6的可移动叶片依赖于低压轴7,高压压缩机3的可移动叶片和高压涡轮5的可移动叶片依赖于高压轴8。发动机进一步包括定子9,其中,轴7和轴8由轴承10支撑,仅示出了轴承10中的一些。此外,在轴7与轴8之间可增加轴承11,并且在该位置应用本发明。
现在参考图2。轴承11可以是滚子轴承19或类似物。轴承11包括在此直接与低压轴7接触的内圈28和通过支撑件12连接到高压轴8的外圈27,支撑件12是分离器,该分离器包括两个主要部件:在此由两个垫圈13a和13b组成的刚性主体13,刚性主体13的内径向表面邻接抵靠轴承11的外圈的抵接表面17,并且刚性主体13的外径向表面邻接抵靠高压轴8的抵接表面18;和被容置在腔15中的阻尼器主体14,腔15由垫圈13a和13b轴向地界定,并且由轴承11的外圈27的抵接表面17和高压轴8的抵接表面18径向地界定。支撑件12进一步包括凸缘16a和16b,凸缘16a和16b通过覆盖垫圈13a和13b将高压轴8连接到轴承11的外圈,并且刚性主体13和阻尼器主体14被安置在凸缘16a与16b之间。发动机的径向方向被标记为R,垂直于X。
刚性主体13的主要特性是在正常操作条件下通过保持轴承11与高压轴8的距离恒定来支撑轴承11,具有由于低弹性引起的减小的变形,但是如果刚性主体13经受通常由于轴中的一个轴、特别是低压轴7发生严重不平衡而导致的异常载荷,则刚性主体13会破裂。阻尼主体14在正常操作期间不起作用,并且仅在刚性主体3破裂时开始操作。阻尼主体14可以以至少沿径向方向R具有间隙的方式容置在腔15中,但是阻尼主体14更有利地被容置在腔15中而没有正间隙,并且在抵接表面17与18之间沿径向方向R具有预应力,使得一旦刚性主体13开始破裂,阻尼主体14就会通过被压缩而被激活。
图3示出了在叶片破裂以及刚性主体13破裂之后设备的状态,如图3所示,发生不平衡的低压轴7由此发生风车般转动(windmilling),该风车般转动使低压轴7相对于高压轴倾斜地安置并且使低压轴7靠近高压轴地移动。阻尼主体14在阻尼主体的圆周的介于高压轴8与轴承11之间的一部分圆周上被按压,但是阻尼主体14防止高压轴8与轴承11彼此靠近移动并且防止系统具有更高的不稳定性,并且保持完好的轴(在此和通常情况下为高压轴8)仅发生小的径向运动并且可以继续操作发动机。
因此,刚性主体13在正常操作期间基本上不会变形,但是在达到为刚性主体设计的载荷阈值时能够完全破裂。更一般地,刚性主体包括早期断裂。或者说该刚性主体是早期断裂部分,其通过诸如通常利用烧结制造的工程陶瓷的材料的微观结构形成早期断裂,烧结赋予工程陶瓷高的机械强度,并且该工程陶瓷也能抵抗高温。材料是非均质的,并且材料的非均质性造成了早期断裂。可通过制造这些具有限定的孔隙度的陶瓷、通过将这些陶瓷安装成具有预应力或通过明智地选择刚性主体13的尺寸来调节破裂阈值。高/宽比接近1的块体优选地用于构建这种刚性主体。或者说该块件是早期断裂部分,其通过刚性主体13的形状形成早期断裂,使得刚性主体能够在剪切中起作用。在这种情况下,将选择均质的材料,通常为金属。多个形状适合于在剪切中起作用。在刚性主体13的具有使得这种早期断裂能够产生的形状不规则性的可能形状中,将涉及到:沿轴向方向X的半球形或弓形形状20(图4);具有弯曲截面的双锥形形状21(图5),该双锥形形状21由具有不同斜率、优选地具有相反方向的两个部分22和23形成,这两个部分22和23分别通向抵接表面17和18并通过形成角度24而在高度一半处相交;仍沿轴向方向X具有倾斜截面的圆锥形形状25(图6);或者具有沿机器的角方向倾斜的柱状物26的结构(图7)。总而言之,刚性主体13的能够产生早期断裂的形状不规则性可以包括在轴向方向X上和/或在垂直于轴向方向X和径向方向R的角方向上的斜率或斜率变化;因此,刚性主体13可以在径向方向上依次包括两个部分,这两个部分的斜率彼此不同。
当刚性主体13的截面不规则且倾斜时,倾斜方向可以是任何方向。如果刚性主体13包括位于轴承11的滚子19或更一般地轴承11的滚动元件的两侧的两个部分,如在所示的实施例中那样,这些部分可以相对于这些滚动元件对称。最后,刚性主体13在轴承11的圆周上通常可以是连续或不连续的。
凸缘16a和16b并不一定具有机械强度作用并且因此可以是柔性的,但是凸缘16a和16b可以有助于轴向地保持轴承11的外圈27。阻尼主体14具有传统的能量耗散功能,并且可以由弹性体或填充有粘性液体的袋组成。支撑件12及其所有组件在圆上可以是连续或不连续的,如同刚性主体13那样。也可以考虑用除了在刚性主体13的两个相对部件之间延伸的腔15之外的其他结构容置阻尼主体14。优选地是,刚性主体13由沿轴向方向X的空体积(或在刚性主体两侧的两个空体积)限制,以使刚性主体13能够在破裂之后被释放。最后,支撑件12可位于轴承11的内部或外部。
由于刚性主体13的刚性,因此本发明的设备对发动机的正常操作没有不利影响。在刚性主体13破裂之后,系统随后经受的阻尼使得在通过自然减速使发动机速度远离可能的不稳定频率的同时使轴间冲击能够受到抑制。
Claims (12)
1.飞行器发动机,所述飞行器发动机包括:沿发动机轴向方向延伸的两个同心轴(7,8)、支撑所述轴中的第一轴(7)的轴承(11)、以及将所述轴承连接到所述轴中的第二轴(8)的支撑件(12),其特征在于,所述支撑件(12)包括机械分离器,所述机械分离器主要由刚性主体(13)和阻尼器主体(14)组成,所述刚性主体通过沿垂直于轴向方向的发动机径向方向的两个相对表面抵接在分别与所述第二轴和所述轴承为一体的两个抵接表面(17,18)上,所述刚性主体能够在待在所述抵接表面之间传递的载荷阈值处破裂,所述阻尼器主体被容置在所述支撑件的由所述抵接表面界定的腔(15)中。
2.根据权利要求1所述的发动机,其特征在于,所述刚性主体由两个部件组成,每个部件界定所述抵接表面之间的所述腔(15)。
3.根据权利要求1或2所述的发动机,其特征在于,所述分离器是环状的。
4.根据权利要求1至3中任一项所述的发动机,其特征在于,所述刚性主体由脆性材料制成。
5.根据权利要求4所述的发动机,其特征在于,所述脆性材料是陶瓷。
6.根据权利要求1至3中任一项所述的发动机,其特征在于,所述刚性主体(13)沿所述径向方向延伸,具有沿所述轴向方向和/或沿垂直于所述轴向方向和所述径向方向的角方向的斜率。
7.根据权利要求6所述的发动机,其特征在于,所述刚性主体(13)沿所述径向方向依次包括两个部分(22,23),所述两个部分中的第一部分的斜率与所述两个部分中的第二部分的斜率不同。
8.根据权利要求1至7中任一项所述的发动机,其特征在于,所述刚性主体(13)由沿所述轴向方向的空体积限制。
9.根据权利要求1至8中任一项所述的发动机,其特征在于,所述阻尼器主体(14)在所述抵接表面(17,18)之间沿所述径向方向被施加预应力。
10.根据权利要求1至9中任一项所述的发动机,其特征在于,所述机械分离器进一步包括在所述第二轴(8)与所述轴承(11)之间延伸的侧部凸缘(16),所述刚性主体和所述阻尼器主体被安置在所述凸缘之间。
11.根据权利要求10所述的发动机,其特征在于,所述凸缘(16a,16b)是柔性的。
12.根据权利要求1至11中任一项所述的发动机,其特征在于,所述发动机包括使所述轴承(11)的相应部分(27,28)分别与所述轴成一体的状态,以及使所述部分之一(27)能够相对于与所述部分之一成一体的轴沿所述径向方向移动并且相对于所述轴(8)受到阻尼的状态。
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FR1700200A FR3063310B1 (fr) | 2017-02-28 | 2017-02-28 | Moteur d'aeronef comprenant un palier entre deux arbres concentriques |
FR1700200 | 2017-02-28 | ||
PCT/FR2018/050445 WO2018158528A1 (fr) | 2017-02-28 | 2018-02-26 | Moteur d'aeronef comprenant un palier entre deux arbres concentriques |
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CN110337532A true CN110337532A (zh) | 2019-10-15 |
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US (1) | US11021992B2 (zh) |
EP (1) | EP3589821B1 (zh) |
CN (1) | CN110337532B (zh) |
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WO (1) | WO2018158528A1 (zh) |
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FR3063310B1 (fr) | 2019-04-26 |
EP3589821A1 (fr) | 2020-01-08 |
FR3063310A1 (fr) | 2018-08-31 |
US20200109642A1 (en) | 2020-04-09 |
CN110337532B (zh) | 2021-12-24 |
EP3589821B1 (fr) | 2020-12-09 |
US11021992B2 (en) | 2021-06-01 |
WO2018158528A1 (fr) | 2018-09-07 |
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