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公开(公告)号：EP3382235A1
公开(公告)日：2018-10-03
申请号：EP17164344.8
申请日：2017-03-31
Applicant: HS Marston Aerospace Limited
Inventor： POLLARD, Berwyn , PHILLIPS, Paul
IPC: F16H57/04
CPC classification number: F28F9/001 , B64D35/00 , F16H57/0417 , F28F2230/00 , F28F2280/02
Abstract: A component 10 that generates or requires heat includes a heat exchanger 16 integrated with the component 10. The component 10 includes a component housing 12 holding functional parts 14 of the component, and the heat exchanger 16 has a heat exchanger housing 18 formed integrally with the component housing 12. There is a first fluid circuit in which a first fluid flows through the component 10 in a heat exchange relationship with the functional parts 14, into the heat exchanger 16 via a first fluid inlet 22, through the heat exchanger 16, out of the heat exchanger 16 via a first fluid outlet 24, and back to the functional parts 14 of the component 10. The heat exchanger 16 has a second fluid inlet 26 and a second fluid outlet 28 for connection into a second fluid circuit in which a second fluid flows from outside of the component 10 into the component housing 12 and into the heat exchanger 16 via the second fluid inlet 26, out of the heat exchanger 16 via the second fluid outlet 28 and out of the component housing 12. The heat exchanger housing 18 contains a removable heat exchanger core 20 for exchange of heat between the first fluid in the first fluid circuit and the second fluid in the second fluid circuit, with the heat exchanger core 20 being separate to the heat exchanger housing 18 and removable from the heat exchanger housing 18 during maintenance operations.
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公开(公告)号：EP3364142A1
公开(公告)日：2018-08-22
申请号：EP17156760.5
申请日：2017-02-17
Applicant: HS Marston Aerospace Limited
Inventor： POLLARD, Berwyn , PHILLIPS, Paul
CPC classification number: F28D9/0062 , B23P15/26 , F02C7/12 , F28D1/0426 , F28D9/0093 , F28D2021/0021 , F28D2021/0026 , F28F3/025 , F28F9/26 , F28F2275/02
Abstract: A heat transfer segment (102) for a curved heat exchanger (101), wherein the heat transfer segment (102) comprises a plurality of enclosure bars (108, 109) that at least partially define two opposite ends (1021, 1022) of the heat transfer segment (102), wherein the two opposite ends (1021, 1022) define respective general planes, characterised in that: the enclosure bars (108, 109) are shaped and arranged such that the general plane of one end (1021, 1022) of the heat transfer segment (102) is not parallel with the general plane of the other end (1022, 1021) of the heat transfer segment (102), such that when said heat transfer segment (102) is joined to an adjacent heat transfer segment in an end-to-end fashion the enclosure bars (108, 109) the heat transfer segment (102) may join to corresponding enclosure bars of the adjacent heat transfer segment thus forming an angular offset between the two adjacent heat transfer segments.
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Patent Agency Ranking
公开(公告)号：EP3406997B1
公开(公告)日：2020-09-23
申请号：EP17172935.3
申请日：2017-05-25
Applicant: HS Marston Aerospace Limited
Inventor： PHILLIPS, Paul , POLLARD, Berwyn
IPC: F28D7/00
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公开(公告)号：EP3364142B1
公开(公告)日：2019-10-02
申请号：EP17156760.5
申请日：2017-02-17
Applicant: HS Marston Aerospace Limited
Inventor： POLLARD, Berwyn , PHILLIPS, Paul
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公开(公告)号：EP3460377A1
公开(公告)日：2019-03-27
申请号：EP17275147.1
申请日：2017-09-21
Applicant: HS Marston Aerospace Limited
Inventor： POLLARD, Berwyn , WILKES, James
Abstract: An external frame 28 for a heat exchanger, the external frame 28 being for holding a heat exchanger core 10; wherein the external frame 28 is a single integrated structure including: inlet and outlet couplings 47 for connection to a first fluid circuit for supply and return of a first fluid to the heat exchanger core 10; a first tank 36 at a first end of the external frame 28 for fluid communication with a first end of the heat exchanger core 10; a second tank 38 at a second end of the external frame 28 for fluid communication with a second end of the heat exchanger core 10; and a gallery 44 extending along the external frame between the first tank 36 and the second tank 38 providing fluid communication between the first tank 36 and the second tank 38; wherein the external frame 28 is arranged to be sealed to the heat exchanger core 10 so that the first fluid flows from the inlet 47, through the heat exchanger core 10 and the tanks 36, 38, and to the outlet 47.
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公开(公告)号：EP3428568A1
公开(公告)日：2019-01-16
申请号：EP17180588.0
申请日：2017-07-10
Applicant: HS Marston Aerospace Limited
Inventor： PHILLIPS, Paul , POLLARD, Berwyn
Abstract: There is provided a fuel tank inerting system for an aircraft. The system comprises: a catalytic heat exchanger 100 comprising a first flow path and a second flow path for heat exchange with the first flow path, wherein the first flow path comprises a plurality of core flow paths 132, 134 each fluidly isolated from one another within the catalytic heat exchanger and each arranged to exchange heat with the second flow path; and a control valve 150 arranged upstream of the first flow path of the catalytic heat exchanger and arranged to selectively control a flow to each of the core flow paths.
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7.发明公开
公开(公告)号：EP3406997A1
公开(公告)日：2018-11-28
申请号：EP17172935.3
申请日：2017-05-25
Applicant: HS Marston Aerospace Limited
Inventor： PHILLIPS, Paul , POLLARD, Berwyn
IPC: F28D7/00
Abstract: A counterflow heat transfer system comprises a heat exchanger and a flow controller arranged to convey a first fluid through the heat exchanger in a first flow direction and a second fluid through the heat exchanger in a second counterflow direction. The heat exchanger comprises at least one first thermally conductive tube (4) conveying the first fluid and at least one second thermally conductive tube (6a, 6b) conveying the second fluid. The first and second tubes (4, 6a, 6b) are wound around one another and in contact with one another in an entwined tubular arrangement (2).
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