公开(公告)号：US20200318541A1

公开(公告)日：2020-10-08

申请号：US16451548

申请日：2019-06-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David MENHEERE ,  Richard KOSTKA ,  Steven STRECKER

IPC: F02C7/047

Abstract: An anti-icing system for a gas turbine engine comprises a closed circuit containing a phase-change fluid, at least one heating component for boiling the phase-change fluid, the anti-icing system configured so that the phase-change fluid partially vaporizes to a vapour state when boiled by the at least one heating component. The closed circuit has an anti-icing cavity adapted to be in heat exchange with an anti-icing surface of the gas turbine engine for the phase-change fluid to release heat to the anti-icing surface and condense. A feed conduit(s) has an outlet end in fluid communication with the anti-icing cavity to feed the phase-change fluid in vapour state from heating by the at least one heating component to the anti-icing cavity, and at least one return conduit having an outlet end in fluid communication with the anti-icing cavity to direct condensed phase-change fluid from the anti-icing cavity to the at least one heating component. A method for heating an anti-icing surface of an aircraft is also provided.

公开(公告)号：US20160281656A1

公开(公告)日：2016-09-29

申请号：US14670915

申请日：2015-03-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Daniel ALECU ,  Steven STRECKER ,  Andrew WALZ

IPC: F02M31/16 ,  F02C7/22

Abstract: A fuel system for a gas turbine engine having a combustor that is fed fuel from a fuel tank includes a main fuel line providing fuel flow from the fuel tank to the combustor, at least one pump pumping fuel from the fuel tank to the combustor via a fuel metering unit. The at least one pump includes an ejector pump. The fuel metering unit directs a portion of the fuel into a motive flow line. The motive flow line provides return of the portion of the fuel to the ejector pump. A first heat exchanger and a second heat exchanger are disposed in serial flow communication within the main fuel line between the at least one pump and the fuel metering unit. The second heat exchanger is downstream from the first heat exchanger. The first heat exchanger is a fuel-to-fuel heat exchanger providing heat transfer communication between the main fuel line and the motive flow line. A method of heating fuel in a fuel system of a gas turbine engine is also presented.

Abstract translation: 一种用于具有从燃料箱供给燃料的燃烧器的燃气涡轮发动机的燃料系统包括：主燃料管路，其将燃料流从燃料箱提供到燃烧器，至少一个泵经由燃料经由 燃油计量单元。 所述至少一个泵包括喷射泵。 燃料计量单元将一部分燃料引导到动力流动管线中。 动力流动线路将燃料的一部分返回到喷射泵。 第一热交换器和第二热交换器在至少一个泵和燃料计量单元之间的主燃料管线内串联流动连通地设置。 第二热交换器在第一热交换器的下游。 第一热交换器是提供主燃料管线和动力流动管线之间的传热连通的燃料 - 燃料热交换器。 还提出了一种在燃气涡轮发动机的燃料系统中加热燃料的方法。