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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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Patent Agency Ranking
公开(公告)号：US20230287950A1
公开(公告)日：2023-09-14
申请号：US18062953
申请日：2022-12-07
Applicant: Honeywell International Inc.
CPC classification number: F16D65/84 , F16D66/026 , F16D65/18 , B60T17/22 , H01L35/02 , H01L35/30 , F16D2066/003
Abstract: A system including a magnet configured to move in response to a movement of a wear pin indicator of a brake assembly of a vehicle. A sensor is configured to generate position data corresponding to the magnet. The position data is indicative of a position and/or movement of the wear pin indicator. The system includes a thermoelectric generator configured to generate an electrical signal based on an operation of the brake assembly. The thermoelectric generator is configured to deliver at least a portion of the electrical signal to the sensor. The system includes a mounting bracket configured to mechanically couple a sensor housing to an actuator housing of the brake assembly. The mounting bracket is configured to provide heat to the thermoelectric generator when the mounting bracket mechanically couples the sensor housing and the actuator housing.
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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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公开(公告)号：US12129859B1
公开(公告)日：2024-10-29
申请号：US18409441
申请日：2024-01-10
Applicant: Honeywell International Inc.
Inventor： Raghavendra Gattu , Chandiran Jayamurugan , Bharath Chandra G , Niall McCabe
CPC classification number: F04D17/12 , F04D29/286 , F04D29/442 , F04D29/444
Abstract: A compressor comprising: a first compressor wheel comprising a first chamber configured to retain a medium, a first impeller disposed within the first chamber and configured to revolve around a longitudinal axis of the compressor, and a first diffuser coupled to the first chamber; and a second compressor wheel comprising a second chamber disposed radially outwards of the first chamber relative to the longitudinal axis, wherein the second chamber is configured to receive the outputted medium from the first chamber, a second impeller disposed within the second chamber and configured to revolve around the longitudinal axis of the compressor within the second chamber, and a second diffuser coupled to the second chamber, wherein each blade of the first impeller defines a fillet extending along an outer edge of the blade, and wherein a width of the fillet along a surface of the respective blade varies along the longitudinal axis.
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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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