公开(公告)号：US20220074368A1

公开(公告)日：2022-03-10

申请号：US17398817

申请日：2021-08-10

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios KYRITSIS ,  Maurice BRISTOW ,  Peter LOFTUS

IPC: F02K3/075 ,  F02C7/36 ,  F02C9/28 ,  F02C9/18 ,  F02K3/06

Abstract: A turbofan gas turbine engine having a bypass duct, and a bypass airflow measurement system. The bypass airflow measurement system comprises: at least one acoustic transmitter configured to transmit an acoustic waveform across the bypass duct of the gas turbine engine though which a bypass airflow passes to at least one acoustic receiver; where the at least one acoustic transmitter and the at least one acoustic receiver are located on an axial plane that is substantially perpendicular to the bypass flow. A method of measuring bypass airflow properties of a turbofan gas turbine engine is also described.

公开(公告)号：US20180245514A1

公开(公告)日：2018-08-30

申请号：US15877930

申请日：2018-01-23

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios KYRITSIS

IPC: F02C7/055 ,  F02K3/06

CPC classification number: F02C7/055 ,  F01D25/285 ,  F02K3/06 ,  F05D2220/32 ,  F05D2260/83

Abstract: A gas turbine engine arrangement comprising a gas turbine engine and an inlet screen. The gas turbine engine comprises an engine core comprising an inlet having a radial extent extending from an engine longitudinal axis to a first radial position, and a fan duct comprising an inlet having a radial extent extending from the first radial position to a fan casing, the inlet screen comprising an at least part annular porous grid radially extending across at least part of the radial extent of the fan duct inlet, and not extending across any substantial part of the radial extent of the core inlet.

公开(公告)号：US20230235700A1

公开(公告)日：2023-07-27

申请号：US18083174

申请日：2022-12-16

Applicant: ROLLS-ROYCE plc

Inventor： Peter D SMOUT ,  Vasileios KYRITSIS ,  Benjamin J EASTMENT ,  Paul S MCCABE ,  Sebastiaan BOTTENHEIM ,  Jason CHETWYND-CHATWIN

IPC: F02C7/141

CPC classification number: F02C7/141 ,  F05D2260/213 ,  F05D2220/323

Abstract: A gas turbine engine comprises a bypass duct and a heat exchanger assembly, the heat exchanger assembly comprising a heat exchanger and a heat exchanger duct having an inlet region, an inflection region and an outlet region. A direction of a centreline of the heat exchanger duct has a tangential component with respect to a principal rotational axis of the gas turbine engine at one or more of the inlet region, the inflection region and the outlet region. The heat exchanger is disposed within the inflection region and configured to transfer heat generated by the gas turbine engine into the flow of air as it passes through the inflection region.

公开(公告)号：US20190391047A1

公开(公告)日：2019-12-26

申请号：US16422334

申请日：2019-05-24

Applicant: ROLLS-ROYCE plc

Inventor： Maurice BRISTOW ,  Vasileios KYRITSIS

IPC: G01M15/14 ,  B64F5/60

Abstract: A method of estimating a parameter of a fluid flowing in a passage includes: having a plurality of instruments operable to measure one or more fluid properties flowing in the passage, the plurality of instruments being disposed in the passage and arranged within a common measurement plane; assigning a stream tube to each instrument, each stream tube represents a region of space in the common measurement plane within the passage and each stream tube surrounds one of the plurality of instruments, the stream tubes together correspond to the cross-sectional shape and area of the passage in the common measurement plane; measuring the one or more fluid properties using the instruments to obtain one or more measured values for each stream tube; using the measured value(s) for each stream tube to calculate a derived value for each stream tube; and summing the derived values across all of the stream tubes.

公开(公告)号：US20190389566A1

公开(公告)日：2019-12-26

申请号：US16422231

申请日：2019-05-24

Applicant: ROLLS-ROYCE plc

Inventor： Vasileios KYRITSIS ,  Maurice BRISTOW

IPC: B64C21/02 ,  B64D31/06 ,  B64D31/14 ,  B64C19/02

Abstract: A control system operable includes a modified primary control parameter for an aircraft, the control system includes: a primary control parameter leg configured to output a demand in an aircraft primary control parameter; a primary control parameter compensation leg configured to receive a change in absolute levels and/or spatial distributions of swirl angle and/or fan pressure at a primary control parameter relative to a reference and convert the change into the primary control parameter; a processor adapted to receive the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; compare the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; and generate a modified primary control parameter for the aircraft.