公开(公告)号：US20210190318A1

公开(公告)日：2021-06-24

申请号：US16723404

申请日：2019-12-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael R. Kracum ,  David C. Jarmon

IPC: F23R3/00 ,  F02C7/18

Abstract: A method of making an ceramic article according to an exemplary embodiment of this disclosure, among other possible things includes arranging fiber plies into a preform, inserting one or more sacrificial springs to the preform, infiltrating the preform with a matrix material to form an article, and thermally degrading the one or more sacrificial springs to form cooling holes. A ceramic article and a gas turbine engine component are also disclosed.

公开(公告)号：US10406556B2

公开(公告)日：2019-09-10

申请号：US15029312

申请日：2014-10-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David C. Jarmon

IPC: C03B19/02 ,  B05D1/00 ,  B05C1/00

Abstract: One exemplary embodiment of this disclosure relates to a transfer molding assembly including a chamber, a die within the chamber, a first gas control device configured to provide a first gas into the chamber, and a second gas control device configured to provide a second gas into the die.

公开(公告)号：US10371011B2

公开(公告)日：2019-08-06

申请号：US14686842

申请日：2015-04-15

Applicant: United Technologies Corporation

Inventor： David C. Jarmon

IPC: F01D25/28 ,  C04B35/565 ,  C04B35/571 ,  C04B35/573 ,  C04B35/634 ,  C04B35/638 ,  C04B35/80 ,  C04B35/83 ,  C04B37/00 ,  F01D11/00 ,  F01D25/24 ,  F23R3/00 ,  F23R3/28 ,  F23R3/60 ,  F01D5/00 ,  F01D9/00 ,  F01D25/00 ,  F01D25/30 ,  F02K1/82 ,  B28B1/00 ,  B28B11/12 ,  C04B35/622 ,  C04B35/64 ,  C04B35/76 ,  D03D25/00 ,  F02C7/28

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

公开(公告)号：US10308818B2

公开(公告)日：2019-06-04

申请号：US15158640

申请日：2016-05-19

Applicant: United Technologies Corporation

Inventor： Xia Tang ,  David C. Jarmon ,  Paul Sheedy ,  Virginia H. Faustino

IPC: B32B15/04 ,  B32B17/06 ,  C09D5/08 ,  B01J20/02 ,  B01J20/10 ,  C03C17/02 ,  C23C24/08 ,  C23C30/00

Abstract: An article comprising a substrate and at least one coating layer disposed on the substrate. The coating layer includes a silicate glass matrix, an oxygen scavenger phase dispersed through the silicate glass matrix, and at least one metal in metallic form.

公开(公告)号：US20180155252A1

公开(公告)日：2018-06-07

申请号：US15874284

申请日：2018-01-18

Applicant: United Technologies Corporation

Inventor： Paul Sheedy ,  David C. Jarmon

IPC: C04B35/82 ,  C04B35/80 ,  C04B35/76 ,  C04B35/14 ,  C04B35/83

CPC classification number: C04B35/82 ,  C04B35/14 ,  C04B35/76 ,  C04B35/80 ,  C04B35/83 ,  C04B2235/3418 ,  C04B2235/421 ,  C04B2235/5284 ,  C04B2235/5288 ,  C04B2235/606

Abstract: Methods for fabricating a ceramic matrix composite are disclosed. A fiber preform may be placed in a mold. An aqueous solution may be added to the fiber preform. The aqueous solution may include water, carbon nanotubes, and a binder. The preform may be frozen. Freezing the preform may cause the water to expand and separate fibers in the fiber preform. The carbon nanotubes may bond to the fibers. The preform may be freeze dried to remove the water. The preform may then be processed according to standard CMC process.

公开(公告)号：US20160265389A1

公开(公告)日：2016-09-15

申请号：US14686842

申请日：2015-04-15

Applicant: United Technologies Corporation

Inventor： David C. Jarmon

IPC: F01D25/28 ,  F02C7/28 ,  B28B1/00 ,  D03D25/00 ,  C04B35/76 ,  C04B35/622 ,  C04B35/64 ,  F23R3/00 ,  B28B11/12

CPC classification number: F01D25/28 ,  B28B1/001 ,  B28B1/002 ,  B28B11/12 ,  C04B35/01 ,  C04B35/565 ,  C04B35/571 ,  C04B35/573 ,  C04B35/62227 ,  C04B35/634 ,  C04B35/638 ,  C04B35/64 ,  C04B35/76 ,  C04B35/803 ,  C04B35/806 ,  C04B35/83 ,  C04B37/001 ,  C04B2235/48 ,  C04B2235/5208 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/5252 ,  C04B2235/5256 ,  C04B2235/612 ,  C04B2235/614 ,  C04B2235/616 ,  C04B2237/38 ,  C04B2237/385 ,  C04B2237/60 ,  C04B2237/61 ,  C04B2237/80 ,  C04B2237/84 ,  D03D25/005 ,  F01D5/00 ,  F01D9/00 ,  F01D11/00 ,  F01D25/00 ,  F01D25/005 ,  F01D25/243 ,  F01D25/246 ,  F01D25/30 ,  F02C7/28 ,  F02K1/822 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2230/314 ,  F05D2240/91 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2300/6033 ,  F23M2900/05004 ,  F23R3/002 ,  F23R3/007 ,  F23R3/283 ,  F23R3/60 ,  Y02T50/672 ,  Y02T50/675 ,  Y02T50/6765

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Abstract translation: 一种形成用于陶瓷基体复合部件的整体紧固件的方法包括以下步骤：形成纤维预制件，将聚合物材料施加到纤维预制件上以形成刚性预成型结构，在刚性预成型结构中加工开口，形成纤维紧固件 将纤维紧固件插入开口中，去除聚合物材料，并将基质材料浸入刚性预成型结构和纤维紧固件中以形成具有整体紧固件的陶瓷基复合材料部件。 还公开了一种燃气涡轮发动机。

公开(公告)号：US20200147835A1

公开(公告)日：2020-05-14

申请号：US16744720

申请日：2020-01-16

Applicant: United Technologies Corporation

Inventor： David C. Jarmon

IPC: B28B23/00 ,  F02K1/82 ,  C04B35/80 ,  F01D11/00 ,  F23R3/28 ,  C04B35/83 ,  F01D25/24 ,  F01D25/30 ,  F01D9/00 ,  F01D25/00 ,  F23R3/60 ,  C04B35/565 ,  F23R3/00 ,  C04B35/571 ,  C04B37/00 ,  F01D5/00 ,  F02C7/20 ,  B29C70/02

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

公开(公告)号：US10427984B2

公开(公告)日：2019-10-01

申请号：US15874284

申请日：2018-01-18

Applicant: United Technologies Corporation

Inventor： Paul Sheedy ,  David C. Jarmon

IPC: C04B35/82 ,  C04B35/80 ,  C04B35/76 ,  C04B35/14 ,  C04B35/83

Abstract: Methods for fabricating a ceramic matrix composite are disclosed. A fiber preform may be placed in a mold. An aqueous solution may be added to the fiber preform. The aqueous solution may include water, carbon nanotubes, and a binder. The preform may be frozen. Freezing the preform may cause the water to expand and separate fibers in the fiber preform. The carbon nanotubes may bond to the fibers. The preform may be freeze dried to remove the water. The preform may then be processed according to standard CMC process.

公开(公告)号：US20180142970A1

公开(公告)日：2018-05-24

申请号：US15866882

申请日：2018-01-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David C. Jarmon

IPC: F28F21/04 ,  F28F1/16 ,  F28D7/10 ,  F28D7/00 ,  B23P15/26 ,  F28F1/00 ,  F28F21/08

CPC classification number: F28F21/04 ,  B23P15/26 ,  F28D7/0008 ,  F28D7/103 ,  F28F1/003 ,  F28F1/16 ,  F28F21/08 ,  F28F2265/26 ,  Y10T29/49361 ,  Y10T29/49377

Abstract: The heat exchanger (10) includes a ceramic matrix composite (12) (stable at temperatures up to 1,650° C.) surrounding and defining a hot fluid conduit (14). A hardenable material (18) having a high thermal conductivity is formed into a heat transfer layer (16) surrounding the ceramic matrix composite (12). A metal pipe (20) is coextensive with the heat transfer layer (16) and defines at least a portion (22) of at least one cool fluid passage (24, 34, 54) defined adjacent to and in heat exchange relationship with the heat transfer layer (16) so that a fluid passing through the cool fluid passage (24, 34, 54) absorbs heat passing through the heat transfer layer (16) from the hot fluid passing through the hot fluid conduit (14).

公开(公告)号：US20160229756A1

公开(公告)日：2016-08-11

申请号：US15022521

申请日：2014-09-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David C. Jarmon ,  William K. Tredway

IPC: C04B35/82 ,  B28B1/52 ,  B28B1/42

CPC classification number: C04B35/82 ,  B28B1/42 ,  B28B1/52 ,  C03B23/006 ,  C03C14/002 ,  C03C2214/02 ,  C03C2214/30

Abstract: An apparatus for making a composite article includes a monofilament feed track adapted to carry a spaced array of ceramic monofilament strands, a fiber yarn feed track adapted to carry a spaced array of fiber yarn tows impregnated with a plurality of glass particulates, a mandrel, and a heater assembly. The mandrel is adapted to wind together individual glass-impregnated fiber yarn strands and individual ceramic monofilament strands to form a dual-fiber weave. The heater assembly is adapted to heat at least the glass particulates such that pressure from the wound array of ceramic monofilaments is sufficient to consolidate the glass particulates and the dual-fiber weave into a dual-fiber ceramic matrix composite (CMC).

Abstract translation: 用于制造复合制品的装置包括适于承载间隔开的陶瓷单丝股线阵列的单丝进给轨道，适于承载浸渍有多个玻璃微粒的纤维丝束间隔阵列的纤维纱线进给轨道，心轴和 加热器组件。 心轴适于将各个玻璃浸渍的纤维纱线和单独的陶瓷单丝股线组合在一起以形成双纤维编织。 加热器组件适于加热至少玻璃颗粒，使得来自陶瓷单丝的卷绕阵列的压力足以将玻璃颗粒和双纤维编织成双纤维陶瓷基质复合材料（CMC）。