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公开(公告)号：US20160356173A1
公开(公告)日：2016-12-08
申请号：US15155359
申请日：2016-05-16
Applicant: ROLLS-ROYCE plc
Inventor： David M. LONGWORTH , Jonathan A. JARVIS , Jonathan A. CHERRY , Hugh J. BLAKEMORE , John R. WEBSTER
CPC classification number: F01D17/162 , F04D29/563 , F05D2300/505
Abstract: An actuation arrangement for effecting actuation of pivotable vane, for example, variable inlet guide vane in gas turbine engine. The actuation arrangement includes an actuator having a support plate and pivotable plate. The pivotable plate is fixedly connected to pivotable vane and pivotable plate and pivotable vane are pivotable about a pivot axis. The actuator further includes at least one actuation element having a length extending from support plate to proximal a transverse edge portion of pivotable plate substantially perpendicular to pivot axis. The or each actuation element is fixedly connected to each of the support and pivotable plates and formed of a material that changes dimension upon application of external energy. Thus, upon application of external energy, for example, heat, a change in length of the or each actuation element occurs such that change in length effects pivoting of pivotable plate and pivotable vane about the pivot axis.
Abstract translation: 用于实现可转动叶片的致动的致动装置，例如燃气涡轮发动机中的可变入口引导叶片。 致动装置包括具有支撑板和可枢转板的致动器。 可枢转板固定地连接到可枢转的叶片和可枢转的板上，并且可枢转的叶片围绕枢转轴线可枢转。 致动器还包括至少一个致动元件，其具有从支撑板延伸到基本垂直于枢转轴线的可枢转板的横向边缘部分的长度的长度。 该或每个致动元件固定地连接到每个支撑和可枢转板，并且由施加外部能量而改变尺寸的材料形成。 因此，当施加外部能量（例如热量）时，发生这种或每个致动元件的长度的变化，使得长度的变化影响可枢转板和枢转叶片围绕枢转轴线的枢转。
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公开(公告)号：US20230167768A1
公开(公告)日：2023-06-01
申请号：US17940055
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Jonathan A. CHERRY , Paul R. DAVIES , David A. JONES , Andrew J. NEWMAN , Benjamin J. SELLERS , Stephen J. BRADBROOK
CPC classification number: F02C7/12 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/213
Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.
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公开(公告)号：US20220205389A1
公开(公告)日：2022-06-30
申请号：US17494738
申请日：2021-10-05
Applicant: ROLLS-ROYCE plc
Inventor： Paul M. HIELD , Jonathan A. CHERRY , Thomas S. BINNINGTON
Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module comprises a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. The heat exchanger module has a square axial cross-sectional profile, where a side length of the square cross-section is D.
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