公开(公告)号：US11702189B1

公开(公告)日：2023-07-18

申请号：US17890063

申请日：2022-08-17

Applicant: Textron Innovations Inc.

Inventor： John Robert Wittmaak ,  Alan Hisashi Steinert

IPC: B64C11/30 ,  F04D29/36 ,  B64C11/06 ,  B64C11/44 ,  B64C11/34

CPC classification number: B64C11/44 ,  B64C11/06 ,  B64C11/34 ,  F04D29/362

Abstract: A blade-pitch change mechanism includes a motor comprising a rotating motor shaft and a housing, a solenoid coupled to a first end of the rotating motor shaft and to the housing, and a hub coupled with a second end of the rotating motor shaft. The hub includes a cylindrical puck having formed therein a gated castellated groove and connected to the second end of the rotating motor shaft and a cylindrical blade-pitch hub selectively couplable with the cylindrical puck via a plurality of drive pins and having formed therein a blade-pitch adjustment groove.

公开(公告)号：US11814164B1

公开(公告)日：2023-11-14

申请号：US17729646

申请日：2022-04-26

Applicant: Textron Innovations Inc.

Inventor： John Robert Wittmaak ,  Alan Hisashi Steinert

IPC: B64C29/00 ,  B64C11/30 ,  B64D27/24

CPC classification number: B64C29/0033 ,  B64C11/301 ,  B64C11/305 ,  B64D27/24

Abstract: A method of verifying operation of an aircraft in a pre-defined flight mode includes operating the aircraft in a first flight mode, commanding the aircraft to transition to a second flight mode, evaluating a plurality of motor performance parameters, and based on values of the plurality of motor performance parameters, determining whether the aircraft has successfully transitioned to the second flight mode.

公开(公告)号：US20220194619A1

公开(公告)日：2022-06-23

申请号：US17686347

申请日：2022-03-03

Applicant: Textron Innovations Inc.

Inventor： Alan Hisashi Steinert ,  Thomas Dewey Parsons ,  Troy Cyril Schank

IPC: B64D35/02 ,  B64D27/20 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F04D25/16

Abstract: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.

公开(公告)号：US11939077B2

公开(公告)日：2024-03-26

申请号：US17686347

申请日：2022-03-03

Applicant: Textron Innovations Inc.

Inventor： Alan Hisashi Steinert ,  Thomas Dewey Parsons ,  Troy Cyril Schank

IPC: B64D35/02 ,  B64D27/20 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F04D25/16 ,  B64C29/00

CPC classification number: B64D35/02 ,  B64D27/20 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F04D25/166 ,  B64C29/0033 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/407 ,  F05D2260/408

Abstract: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.