公开(公告)号：US20250163823A1

公开(公告)日：2025-05-22

申请号：US19033023

申请日：2025-01-21

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Daniel Bernard Kupratis ,  Michael Romero

IPC: F01D15/10 ,  B64D27/02 ,  F02C7/277 ,  F02C9/26

Abstract: A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine and boosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines, such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine.

公开(公告)号：US20250043730A1

公开(公告)日：2025-02-06

申请号：US18919910

申请日：2024-10-18

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Lance L. Smith ,  Neal R. Herring ,  Christopher J. Hanlon

IPC: F02C7/32 ,  F02C7/141 ,  F02C7/18

Abstract: A gas turbine engine includes a turbine section located at an engine central longitudinal axis, a combustor configured to drive rotation of the turbine with combustion products, and a compressor section coupled to the turbine section at the engine central longitudinal axis and driven by the turbine section. An auxiliary compressor is located fluidly between the compressor section and the combustor such that an airflow exiting the compressor section is directed toward the auxiliary compressor. The auxiliary compressor is driven independently from the compressor section and is configured to output the airflow toward the combustor.

公开(公告)号：US12196137B2

公开(公告)日：2025-01-14

申请号：US17345205

申请日：2021-06-11

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Lance L. Smith ,  Neal R. Herring ,  Christopher J. Hanlon

IPC: F02C7/32 ,  F02C7/141 ,  F02C7/18

Abstract: A gas turbine engine includes a turbine section located at an engine central longitudinal axis, a combustor configured to drive rotation of the turbine with combustion products, and a compressor section coupled to the turbine section at the engine central longitudinal axis and driven by the turbine section. An auxiliary compressor is located fluidly between the compressor section and the combustor such that an airflow exiting the compressor section is directed toward the auxiliary compressor. The auxiliary compressor is driven independently from the compressor section and is configured to output the airflow toward the combustor.

公开(公告)号：US12187448B2

公开(公告)日：2025-01-07

申请号：US17396077

申请日：2021-08-06

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Keith J. Kucinskas

IPC: B64D31/06 ,  B60L50/60 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C9/00

Abstract: Examples described herein provide a computer-implemented method that includes providing the hybrid electric engine, the hybrid electric engine having a gas generating core and an electric machine powered by electric energy. The method further includes determining, by a processing device, whether a use of the electric energy will increase time on wing of the hybrid electric engine of the aircraft a threshold amount. The method further includes, responsive to determining that the use of energy will increase time on wing the threshold amount, apportioning the electric energy from a battery system of the aircraft to increase the time on wing.

公开(公告)号：US20250121947A1

公开(公告)日：2025-04-17

申请号：US18999269

申请日：2024-12-23

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Keith J. Kucinskas

IPC: B64D31/06 ,  B60L50/60 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C9/00

Abstract: Examples described herein provide a computer-implemented method that includes providing the hybrid electric engine, the hybrid electric engine having a gas generating core and an electric machine powered by electric energy. The method further includes determining, by a processing device, whether a use of the electric energy will increase time on wing of the hybrid electric engine of the aircraft a threshold amount. The method further includes, responsive to determining that the use of energy will increase time on wing the threshold amount, apportioning the electric energy from a battery system of the aircraft to increase the time on wing.

公开(公告)号：US11999498B2

公开(公告)日：2024-06-04

申请号：US17517936

申请日：2021-11-03

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Sorin Bengea

IPC: B64D31/00 ,  B64D41/00 ,  F01D15/10 ,  F01D17/16

CPC classification number: B64D31/00 ,  B64D41/00 ,  F01D15/10 ,  F01D17/162 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/57 ,  F05D2260/70 ,  F05D2260/81 ,  F05D2270/20

Abstract: An aspect includes a method of variable cycle compensation in a gas turbine engine. An electric component can be adjusted to compensate for a power change induced by an actuation system by operating the electric component as an electric motor to compensate for an increase in power absorption or a decrease in power production of a turbomachinery of the gas turbine engine. The actuation system is configured to adjust a variable cycle of the turbomachinery by adjusting power absorption or power production, and the electric component can be configured to add or subtract torque to a shaft of the gas turbine engine. The electric component can be operated as an electric generator to compensate for an increase in power production or a decrease in power absorption of the turbomachinery.