公开(公告)号：WO2015142395A3

公开(公告)日：2015-11-19

申请号：PCT/US2014070278

申请日：2014-12-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALARCON ANDREW G ,  TATTON ROYCE E ,  FORD BARRY M ,  LI LINDA S ,  TURNER MATTHEW A

IPC: F01D5/02 ,  F02K3/06

CPC classification number: F01D25/005 ,  B29C70/12 ,  B29D99/0025 ,  B29K2105/12 ,  F01D11/008 ,  F02K3/06 ,  F04D29/325 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2300/123 ,  F05D2300/2102 ,  F05D2300/224 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.

Abstract translation: 本公开总体上涉及用于燃气涡轮发动机的风扇叶片平台领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩的短切纤维风扇叶片平台。

公开(公告)号：EP2932047A4

公开(公告)日：2015-12-09

申请号：EP13862661

申请日：2013-11-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALARCON ANDREW G ,  TATTON ROYCE E

IPC: F01D11/08

CPC classification number: F01D11/008 ,  F01D5/3007 ,  F05D2220/36 ,  F05D2250/75 ,  F05D2300/437 ,  Y02T50/673

公开(公告)号：EP2971568A4

公开(公告)日：2016-11-23

申请号：EP14769841

申请日：2014-02-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TATTON ROYCE E

IPC: F01D5/30 ,  F01D11/00 ,  F04D29/08

CPC classification number: F01D11/008 ,  F01D5/3007 ,  F01D5/3053 ,  F01D11/006 ,  F04D29/083 ,  F04D29/322 ,  F05D2220/36 ,  F05D2240/80 ,  Y02T50/673

Abstract: A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.