公开(公告)号：US20210215120A1

公开(公告)日：2021-07-15

申请号：US17217048

申请日：2021-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Constantine Baltas

IPC: F02K1/15 ,  F02K1/06 ,  F02K3/06

Abstract: A turbofan gas turbine engine includes a core engine within a core nacelle, a fan nacelle at least partially surrounding the core nacelle to define a bypass flow path and a variable fan nozzle exit area for bypass flow, and a pylon variable area flow system which operates to effect the bypass flow. A method of operating a turbofan gas turbine engine is also disclosed.

公开(公告)号：USRE48980E1

公开(公告)日：2022-03-22

申请号：US17011619

申请日：2020-09-03

Applicant: Raytheon Technologies Corporation

Inventor： Jonathan Gilson ,  Constantine Baltas

IPC: F02C7/045 ,  F02K1/82 ,  F02C7/24 ,  F01D25/24 ,  F02C3/107

Abstract: A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.

公开(公告)号：US10989143B2

公开(公告)日：2021-04-27

申请号：US15889304

申请日：2018-02-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Constantine Baltas

IPC: F02K1/06 ,  F02K1/15 ,  F02K3/06 ,  F02K1/12 ,  F02K3/075 ,  F02C3/107

Abstract: A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, and a pylon variable area flow system. A fan is driven by the gear system. The variable area flow system operates to effect the bypass flow.