公开(公告)号：EP2920072A4

公开(公告)日：2016-08-10

申请号：EP13854460

申请日：2013-11-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WORTH EDWIN M ,  TILLMAN THOMAS G ,  SCHWARZ FREDERICK M

IPC: F01D5/14 ,  B23P15/04

CPC classification number: F01D5/18 ,  F01D5/141 ,  F01D5/145 ,  F01D5/147 ,  F01D5/225 ,  F01D5/28 ,  F02C7/36 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/31 ,  F05D2250/181 ,  F05D2250/311 ,  F05D2250/321 ,  F05D2250/322 ,  F05D2250/62 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/516 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336

Abstract: A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension.

Abstract translation: 风扇叶片包括具有在前缘和后缘之间延伸的翼型件的主体。 风扇叶片具有由盖封闭的通道中的至少一个以及覆盖前缘和后缘中的至少一个的端盖。 盖和端盖中的至少一个具有一对相对的端部。 限定从所述翼型件的吸入壁和压力壁中的至少一个延伸到所述相对端中的一个的盖和端盖中的一个的外表面，并且所述台阶小于或等于 到约0.010英寸（0.0254厘米）的尺寸。

公开(公告)号：EP1677888A4

公开(公告)日：2008-12-17

申请号：EP04783422

申请日：2004-09-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPADACCINI LOUIS J ,  KASLUSKY SCOTT F ,  TILLMAN THOMAS G ,  DEVALVE TIMOTHY D ,  BERTUCCIOLI LUCA ,  SAHM MICHAEL K ,  HUANG HE ,  BAYT ROBERT L ,  LAMM FOSTER PHILIP ,  SABATINO DANIEL R

IPC: B01D19/00 ,  C10L1/00 ,  B01D61/00 ,  B01D63/08 ,  B01D65/08 ,  B01D69/10 ,  B01D69/12 ,  B01D71/32 ,  B01D71/36 ,  F02C7/12 ,  F02C7/14 ,  F02C7/224

CPC classification number: B01D69/10 ,  B01D19/0031 ,  B01D61/00 ,  B01D63/082 ,  B01D63/084 ,  B01D65/08 ,  B01D2321/2008 ,  F02C7/12 ,  F02C7/14 ,  F02C7/224 ,  Y02T50/672 ,  Y02T50/675

Abstract: A system (10) for the management of thermal transfer in a gas turbine engine (14) includes a heat generating sub-system disposed in operable communication with the engine (14), a fuel source (18) configured to supply a fuel, a fuel stabilization unit (16) configured to receive the fuel from the fuel source (18) and to provide the fuel to the engine (14), and a heat exchanger disposed in thermal communication with the fuel to effect the transfer of heat from the heat generating sub-system to the fuel. A method of managing such thermal transfer includes removing oxygen from the fuel in the fuel atabilization unit (16), transferring heat from the heat generating sub-system to the fuel, and combusting the fuel in gas turbine engine (14). System (10) can be used for the thermal management of an aircraft.