公开(公告)号：US20160146023A1

公开(公告)日：2016-05-26

申请号：US14933129

申请日：2015-11-05

Applicant: United Technologies Corporation

Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

IPC: F01D5/30 ,  F01D5/14

CPC classification number: B23P15/006 ,  F01D5/282 ,  F01D5/34 ,  F05D2300/6033

Abstract: A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.

Abstract translation: 构造成用于在燃气涡轮机内操作的推进式发动机转子包括多个间隔开的叶片叶片，周向地固定在外箍型轮缘上。 至少两个翼型叶片具有构造成从轮缘延伸穿过或至少径向向内延伸的整体根部。 编织纤维系统规定，在将纤维和包裹的根部浸入陶瓷或其它复合基质材料中以形成复合环之前，叶片根部被多个编织纤维叉指地包裹。 复合环限定转子的内部主体，包括通过转子的旋转轴线并且具有比转子轮辋更低的质量的孔。 根部之间的机织纤维界面增加了翼型相对于复合环的拉伸载荷能力，并提高了转子的自维持半径。

公开(公告)号：US10648481B2

公开(公告)日：2020-05-12

申请号：US14929701

申请日：2015-11-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

IPC: F02C1/00 ,  F04D29/32 ,  F01D5/02 ,  F01D25/28 ,  F02C3/06

Abstract: A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.

公开(公告)号：US10370971B2

公开(公告)日：2019-08-06

申请号：US14929771

申请日：2015-11-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

IPC: F01D5/02 ,  F01D5/06 ,  F01D5/34 ,  F02C3/04

Abstract: A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.

公开(公告)号：US10029336B2

公开(公告)日：2018-07-24

申请号：US14933129

申请日：2015-11-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

IPC: B23P15/00 ,  F01D5/34 ,  F01D5/28

Abstract: A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.

公开(公告)号：US20160138399A1

公开(公告)日：2016-05-19

申请号：US14929771

申请日：2015-11-02

Applicant: United Technologies Corporation

Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

IPC: F01D5/02 ,  F01D5/34 ,  F02C3/04

CPC classification number: F01D5/02 ,  F01D5/06 ,  F01D5/34 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/60 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2300/224 ,  F05D2300/48 ,  F05D2300/603 ,  F05D2300/6032 ,  F05D2300/614 ,  Y02T50/672

Abstract: A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.

Abstract translation: 公开了一种用于燃气涡轮发动机的结构增强转子盘。 转子盘可以包括主体，其包括构造成支撑翼型件（其可以与翼型件分离或一体的）的边缘，设置在轮辋径向内侧的轴向延伸的孔以及连接轮辋和钻孔的径向延伸的腹板 。 孔可以包括轴向外边缘和在外边缘和腹板之间轴向形成的至少一个周向延伸的环形凹部。 转子盘还可以包括保持在环形凹部中的环形圈，并且环形圈可以由与转子盘的主体不同的材料形成，以便增加转子盘的自维持半径。

公开(公告)号：US20160153463A1

公开(公告)日：2016-06-02

申请号：US14929701

申请日：2015-11-02

Applicant: United Technologies Corporation

Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

IPC: F04D29/32 ,  F01D25/28 ,  F02C3/06 ,  F01D5/02

CPC classification number: F04D29/321 ,  F01D5/02 ,  F01D5/066 ,  F01D11/001 ,  F01D25/28 ,  F02C3/06 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2300/603 ,  F05D2300/6032 ,  F05D2300/614 ,  Y02T50/672

Abstract: A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.

Abstract translation: 燃气涡轮发动机的间隔件用纤维增强。 纤维可以用基材固化以形成纤维增强复合材料。 当燃气涡轮发动机运行时，旋转产生能够使包括间隔件在内的某些燃气涡轮发动机部件变形，膨胀，收缩或平移的力。 这些力可能不利地影响燃气轮机的性能和可靠性，特别是当它们不可预测或难以控制时。 用纤维增强间隔物可能会降低系统重量，更紧凑或可配置的内部包装或高度的增强。