公开(公告)号：US20150322800A1

公开(公告)日：2015-11-12

申请号：US14275012

申请日：2014-05-12

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Lorenzo Crosatti ,  Shezan Kanjiyani ,  Don Mittendorf

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/189 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F7/004 ,  F01D5/147 ,  F01D5/183 ,  F01D5/186 ,  F01D5/188 ,  F05D2260/202 ,  F05D2260/203 ,  Y02P10/295 ,  Y02T50/676 ,  Y10T29/49321

Abstract: Gas path components of gas turbine engines and methods for cooling the same using porous medium cooling systems are provided. The gas path component comprises a wall at least partially defining a cooling plenum and a porous medium cooling system. The wall includes a wall surface comprising a gas path surface and an opposing wall surface proximate the cooling plenum. The porous medium cooling system is disposed between the cooling plenum and the opposing wall surface. The porous medium cooling system comprises a perforated baffle and a porous material layer disposed between and adjacent the perforated baffle and the opposing wall surface. The wall includes a plurality of openings in fluid communication with the cooling plenum via the porous medium cooling system.

Abstract translation: 提供燃气涡轮发动机的气路部件和使用多孔介质冷却系统对其进行冷却的方法。 气体路径部件包括至少部分限定冷却气室和多孔介质冷却系统的壁。 该壁包括壁表面，该壁表面包括靠近冷却气室的气体通道表面和相对的壁表面。 多孔介质冷却系统设置在冷却气室和相对的壁表面之间。 多孔介质冷却系统包括穿孔挡板和设置在穿孔挡板和相对的壁表面之间和之间的多孔材料层。 该壁包括多个通过多孔介质冷却系统与冷却气室流体连通的开口。

公开(公告)号：US20150247409A1

公开(公告)日：2015-09-03

申请号：US14713220

申请日：2015-05-15

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Don Mittendorf ,  David K. Jan ,  Jason Smoke ,  Amandine Miner

IPC: F01D5/14 ,  F01D5/28 ,  F01D5/04

CPC classification number: F01D5/147 ,  B23P15/006 ,  F01D5/04 ,  F01D5/045 ,  F01D5/046 ,  F01D5/048 ,  F01D5/066 ,  F01D5/088 ,  F01D5/18 ,  F01D5/187 ,  F01D5/28 ,  F01D5/30 ,  F05D2230/60 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49321 ,  Y10T29/49323 ,  Y10T29/49341

Abstract: Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

Abstract translation: 轴向分离的径向涡轮机的实施例，如用于制造轴向分离的径向涡轮机的方法的实施例。 在一个实施例中，该方法包括以下步骤：将前叶片环连接到前盘，以产生正向涡轮转子，制造后涡轮转子，以及将正向涡轮转子和后涡轮转子设置在轴向邻接的旋转 固定关系以产生轴向分离的径向涡轮机。

公开(公告)号：US20140134353A1

公开(公告)日：2014-05-15

申请号：US13675439

申请日：2012-11-13

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Don Mittendorf

IPC: C22C19/05

CPC classification number: C22C19/05 ,  C22C19/03 ,  C22C19/057 ,  F01D5/28 ,  F05D2300/175

Abstract: A nickel-based super alloy includes, by weight, about 1.5% to about 5.5% chromium, about 8% to about 12% aluminum, about 4% to about 8% tantalum, about 1.5% to about 5.5% tungsten, less than about 1% of one or more of elements selected from a group consisting of carbon, boron, zirconium, yttrium, hafnium, and silicon, and a balance of nickel.

Abstract translation: 一种镍基超级合金包括按重量计约1.5％至约5.5％的铬，约8％至约12％的铝，约4％至约8％的钽，约1.5％至约5.5％的钨，小于约 选自碳，硼，锆，钇，铪和硅中的一种或多种元素的1％，余量为镍。