公开(公告)号：US20200186017A1

公开(公告)日：2020-06-11

申请号：US16212799

申请日：2018-12-07

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric LATULIPE ,  Richard FREER

IPC: H02K29/03 ,  H02K7/116 ,  H02K16/02 ,  F16H1/22

Abstract: An electric machine system described herein comprises a first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors driven using electric power having a first phase. The second electric machine has a plurality of second rotors driven using electric power having a second phase. The second phase differs from the first phase. Each of one or more shafts connects a first rotor with a second rotor. The first rotor is coaxial with and axially spaced apart from the second rotor.

公开(公告)号：US20200186016A1

公开(公告)日：2020-06-11

申请号：US16212797

申请日：2018-12-07

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric LATULIPE ,  Richard FREER

IPC: H02K29/03 ,  H02K7/116 ,  H02K16/02 ,  F16H1/22

Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.

公开(公告)号：US20200083791A1

公开(公告)日：2020-03-12

申请号：US16411484

申请日：2019-05-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric LATULIPE ,  Richard FREER

IPC: H02K41/03 ,  B64D35/08 ,  B64D35/02 ,  H02P6/12 ,  H02K47/04 ,  G08C19/38

Abstract: A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.