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    Float wall combustor panels having airflow distribution features
    11.
    发明授权
    Float wall combustor panels having airflow distribution features 有权

    公开(公告)号：US10267520B2

    公开(公告)日：2019-04-23

    申请号：US15674548

    申请日：2017-08-11

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  Jeffrey T. Morton ,  Alberto A. Mateo

    IPC: F23R3/00 ,  F23R3/16 ,  F23R3/50

    Abstract: Combustor panel bodies with first and second sides, a pin array of cooling pins extending from the first side, with each pin extending a first height from the first side and having a pin diameter, each pin separated from adjacent pins by a pin array separation distance. A structural protrusion extending from the first side with no pins located at a position within a flashing distance that is equal to a protrusion separation distance plus one half of the pin diameter. A location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. A pin array scallop is integrally formed with the structural protrusion forming a reduction in material such that each pin of the array that is closest to the structural protrusion is positioned the pin array separation distance from the structural protrusion.

    IMPINGEMENT COOLING ARRANGEMENT FOR AIRFOILS
    15.
    发明申请
    IMPINGEMENT COOLING ARRANGEMENT FOR AIRFOILS 审中-公开

    公开(公告)号：US20200149409A1

    公开(公告)日：2020-05-14

    申请号：US16734464

    申请日：2020-01-06

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  Jeffrey T. Morton ,  Alberto A. Mateo ,  San Quach ,  Gregory Anselmi

    IPC: F01D5/18 ,  F04D29/58 ,  F04D29/32

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

    Impingement cooling arrangement for airfoils
    16.
    发明授权
    Impingement cooling arrangement for airfoils 有权

    公开(公告)号：US10570748B2

    公开(公告)日：2020-02-25

    申请号：US15866557

    申请日：2018-01-10

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  Jeffrey T. Morton ,  Alberto A. Mateo ,  San Quach ,  Gregory Anselmi

    IPC: F01D5/18 ,  F04D29/32 ,  F04D29/58

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

    DIRECTIONAL COOLING ARRANGEMENT FOR AIRFOILS
    17.
    发明申请
    DIRECTIONAL COOLING ARRANGEMENT FOR AIRFOILS 审中-公开

    公开(公告)号：US20200032656A1

    公开(公告)日：2020-01-30

    申请号：US16419137

    申请日：2019-05-22

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Alberto A. Mateo ,  Jeffrey T. Morton ,  Jason Shenny ,  Gregory Anselmi

    IPC: F01D5/18

    Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

    BALANCE BRACKET
    18.
    发明申请
    BALANCE BRACKET 审中-公开

    公开(公告)号：US20200018188A1

    公开(公告)日：2020-01-16

    申请号：US16031057

    申请日：2018-07-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Alberto A. Mateo ,  Tracy A. Propheter-Hinckley ,  San Quach

    IPC: F01D25/26 ,  F16M13/02 ,  F04D29/54 ,  F01D9/06

    Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.

    Directional cooling arrangement for airfoils
    19.
    发明授权
    Directional cooling arrangement for airfoils 有权

    公开(公告)号：US10370976B2

    公开(公告)日：2019-08-06

    申请号：US15679442

    申请日：2017-08-17

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Alberto A. Mateo ,  Jeffrey T. Morton ,  Jason Shenny ,  Gregory Anselmi

    IPC: F01D5/18

    Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

    DIRECTIONAL COOLING ARRANGEMENT FOR AIRFOILS
    20.
    发明申请
    DIRECTIONAL COOLING ARRANGEMENT FOR AIRFOILS 审中-公开

    公开(公告)号：US20190055845A1

    公开(公告)日：2019-02-21

    申请号：US15679442

    申请日：2017-08-17

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Alberto A. Mateo ,  Jeffrey T. Morton ,  Jason Shenny ,  Gregory Anselmi

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/52 ,  F05D2260/202

    Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

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