公开(公告)号：US20140186166A1

公开(公告)日：2014-07-03

申请号：US13728880

申请日：2012-12-27

Applicant: GENERAL ELECTRIC COMPANY

Inventor： James Michael Kostka

IPC: F01D25/00

CPC classification number: B32B5/024 ,  B29C70/081 ,  B29L2031/7504 ,  B32B5/26 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/02 ,  B32B2262/0276 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/542 ,  B32B2307/544 ,  B32B2307/546 ,  B32B2307/558 ,  B32B2605/18 ,  B64C11/14 ,  F01D5/143 ,  F01D5/146 ,  F01D5/282 ,  F05D2250/232 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

Abstract: An engine component having a monolithic composite body, the body having a continuous fiber portion, a chopped fiber portion, a thermoplastic polymer contained in both the continuous fiber portion and the chopped fiber portion and between the continuous and chopped fiber portions.

Abstract translation: 具有整体复合体的发动机部件，具有连续纤维部分的主体，短切纤维部分，包含在连续纤维部分和短切纤维部分中的热塑性聚合物，以及连续切断的纤维部分之间。

公开(公告)号：US20150258729A1

公开(公告)日：2015-09-17

申请号：US14716327

申请日：2015-05-19

Applicant: General Electric Company

Inventor： Jared Matthew Wolfe ,  James Michael Kostka

IPC: B29C51/26 ,  F16B5/02 ,  F16B5/04 ,  B29C65/02

CPC classification number: B29C51/268 ,  B29C51/002 ,  B29C51/12 ,  B29C65/02 ,  B29C65/06 ,  B29C65/08 ,  B29C65/1412 ,  B29C65/34 ,  B29C65/48 ,  B29C65/562 ,  B29C65/60 ,  B29C66/112 ,  B29C66/131 ,  B29C66/524 ,  B29C66/532 ,  B29C66/61 ,  B29C66/71 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73921 ,  B29C69/001 ,  B29C70/42 ,  B29C70/545 ,  B29K2101/12 ,  B29K2105/0809 ,  B29L2009/00 ,  B29L2031/003 ,  B29L2031/3076 ,  B29L2031/7172 ,  B29L2031/737 ,  F01D25/00 ,  F05D2300/43 ,  F05D2300/603 ,  F16B5/02 ,  F16B5/04 ,  Y02T50/43 ,  Y02T50/672 ,  Y10T29/49789 ,  Y10T29/49826 ,  Y10T29/49947 ,  B29K2071/00 ,  B29K2079/085 ,  B29K2081/04 ,  B29K2307/04 ,  B29K2309/08 ,  B29K2305/00 ,  B29K2309/02 ,  B29K2277/00 ,  B29K2277/10 ,  B29K2301/00

Abstract: Load-bearing structures constructed from polymer matrix composite (PMC) materials, and processes for their production. The structures are produced from at least one shaped panel formed of a continuous fiber reinforcement in a thermoplastic resin matrix. The shaped panel has been thermoformed to have a substantially constant cross-sectional thickness and portions that lie in different planes and are interconnected by one or more bends. The shaped panel is machined to alter its shape, and optionally to produce multiple separate subcomponents therefrom. The machined shaped panel can constitute the entire structure, or the structure can be formed by joining the machined shaped panel with other shaped panels or by joining two or more of the subcomponents. The structure can be installed on an aircraft engine to secure components to the engine.

Abstract translation: 由聚合物基质复合材料（PMC）材料构造的承重结构及其生产工艺。 该结构由至少一个由热塑性树脂基体中的连续纤维增强材料形成的成形板制成。 成形板已被热成型以具有基本恒定的横截面厚度，并且位于不同平面中的部分并且通过一个或多个弯曲相互连接。 加工成形板以改变其形状，并且可选地从其中产生多个单独的子部件。 加工成形的面板可以构成整个结构，或者可以通过将加工的成形面板与其它成形面板接合或者通过接合两个或更多个子部件来形成结构。 该结构可以安装在飞机发动机上，以将部件固定在发动机上。

公开(公告)号：US20160281532A1

公开(公告)日：2016-09-29

申请号：US14666389

申请日：2015-03-24

Applicant: General Electric Company

Inventor： Jeffrey Douglas Rambo ,  William Dwight Gerstler ,  James Michael Kostka ,  John William Moores

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F02C7/14 ,  F02C7/18 ,  F05D2250/71 ,  F05D2260/213 ,  F28D1/0477 ,  F28D2021/0021 ,  F28D2021/0026 ,  F28F1/26

Abstract: A heat exchanger apparatus for a gas turbine engine includes: a plurality of heat exchanger pipes, each pipe having first and second ends; wherein the heat exchanger pipes are disposed in a repeating pattern such that each heat exchanger pipe is joined to at least one other heat exchanger pipe.

Abstract translation: 一种用于燃气涡轮发动机的热交换器装置包括：多个热交换器管，每个管具有第一和第二端; 其中所述热交换器管以重复图案设置，使得每个热交换器管连接到至少一个其它热交换管。

公开(公告)号：US09909448B2

公开(公告)日：2018-03-06

申请号：US14686799

申请日：2015-04-15

Applicant: General Electric Company

Inventor： William Dwight Gerstler ,  James Michael Kostka ,  Jeffrey Douglas Rambo ,  John William Moores

IPC: F01D9/04 ,  F01D25/12 ,  F01D25/18 ,  F01D5/18 ,  F02C7/14

CPC classification number: F01D25/12 ,  F01D5/181 ,  F01D9/04 ,  F01D9/041 ,  F01D25/18 ,  F02C7/14 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/208 ,  F05D2260/232 ,  F28D15/046

Abstract: A heat transfer apparatus for a gas turbine engine includes: a component having a wall structure defining a flow bounding surface; a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid.