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公开(公告)号：US10119404B2
公开(公告)日：2018-11-06
申请号：US14515131
申请日：2014-10-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Balamurugan Srinivasan , Sridharan Reghupathy Narayanan , Karthikeyan Paramanandam , Chandiran Jayamurugan , Malak Fouad Malak
Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
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Patent Agency Ranking
公开(公告)号：US10934856B2
公开(公告)日：2021-03-02
申请号：US16155913
申请日：2018-10-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Balamurugan Srinivasan , Sridharan Reghupathy Narayanan , Karthikeyan Paramanandam , Chandiran Jayamurugan , Malak Fouad Malak
Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
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公开(公告)号：US20190106992A1
公开(公告)日：2019-04-11
申请号：US16155913
申请日：2018-10-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Balamurugan Srinivasan , Sridharan Reghupathy Narayanan , Karthikeyan Paramanandam , Chandiran Jayamurugan , Malak Fouad Malak
Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
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4.发明授权公开(公告)号：US12238854B2
公开(公告)日：2025-02-25
申请号：US18049565
申请日：2022-10-25
Applicant: Honeywell International Inc.
Inventor： Karthikeyan Paramanandam , Pedro Luis Lebron
IPC: H05K1/02
Abstract: An electronic assembly comprises a printed circuit board including a plurality of stacked layers, wherein the stacked layers comprise a plurality of conductive layers, a plurality of dielectric layers respectively interposed between the conductive layers, and one or more phase change material layers interposed between at least one pair of the dielectric layers or at least one pair of the conductive layers. During a phase change, the one or more phase change material layers are configured to absorb thermal energy at a phase transition temperature to provide enhanced cooling of the printed circuit board. In some embodiments, the printed circuit board can be a metal core printed circuit board.
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5.发明公开公开(公告)号：US20240080966A1
公开(公告)日：2024-03-07
申请号：US18049565
申请日：2022-10-25
Applicant: Honeywell International Inc.
Inventor： Karthikeyan Paramanandam , Pedro Luis Lebron
IPC: H05K1/02
CPC classification number: H05K1/0212 , H05K1/0298
Abstract: An electronic assembly comprises a printed circuit board including a plurality of stacked layers, wherein the stacked layers comprise a plurality of conductive layers, a plurality of dielectric layers respectively interposed between the conductive layers, and one or more phase change material layers interposed between at least one pair of the dielectric layers or at least one pair of the conductive layers. During a phase change, the one or more phase change material layers are configured to absorb thermal energy at a phase transition temperature to provide enhanced cooling of the printed circuit board. In some embodiments, the printed circuit board can be a metal core printed circuit board.
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公开(公告)号：US20160108740A1
公开(公告)日：2016-04-21
申请号：US14515131
申请日：2014-10-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Balamurugan Srinivasan , Sridharan Reghupathy Narayanan , Karthikeyan Paramanandam , Chandiran Jayamurugan , Malak Fouad Malak
CPC classification number: F01D5/187 , F01D5/147 , F01D5/188 , F02C3/04 , F02C7/04 , F02C7/18 , F05D2220/32 , F05D2240/303 , F05D2240/35 , F05D2260/201 , F05D2260/2214 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
Abstract translation: 用于燃气涡轮发动机的翼型包括具有第一侧壁和在前缘连接的第二侧壁和后缘的主体，第一侧壁具有第一内表面，第二侧壁具有第二内表面。 翼型件还包括设置在主体内部并在第一内表面和第二内表面之间延伸以限定供给通道和前缘通道的内壁。 内壁限定多个冷却孔，以将冷却空气从供应通道引导到前缘通道，使得冷却空气冲击前缘。 所述翼型件还包括形成在所述第一内表面中的第一多个槽，所述第一多个槽在所述前缘通道内沿弦向延伸。
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