公开(公告)号：US10047625B2

公开(公告)日：2018-08-14

申请号：US14401004

申请日：2014-02-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Royce E. Tatton

IPC: F01D11/00 ,  F01D5/30 ,  F04D29/08 ,  F04D29/32

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.

公开(公告)号：US09976426B2

公开(公告)日：2018-05-22

申请号：US14805081

申请日：2015-07-21

Applicant: United Technologies Corporation

Inventor： Matthew A. Turner ,  Royce E. Tatton ,  Kristin Wood ,  Matthew Satterwhite

IPC: F01D5/22 ,  F01D11/00 ,  B29C70/68 ,  B29C70/70 ,  B29C70/84 ,  B29C70/86 ,  F01D5/02 ,  B29K309/08 ,  B29K619/00 ,  B29K627/12 ,  B29K707/04 ,  B29L31/08

CPC classification number: F01D5/225 ,  B29C70/682 ,  B29C70/70 ,  B29C70/84 ,  B29C70/865 ,  B29K2309/08 ,  B29K2619/00 ,  B29K2627/12 ,  B29K2707/04 ,  B29L2031/082 ,  F01D5/02 ,  F01D11/008 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2300/431 ,  F05D2300/432 ,  F05D2300/603 ,  Y02T50/672

Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.