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公开(公告)号：US11168571B2
公开(公告)日：2021-11-09
申请号：US16745930
申请日：2020-01-17
Applicant: United Technologies Corporation
Inventor： David A. Niezelski , Timothy J. Jennings , Bret M. Teller , John McBrien , Thomas N. Slavens
Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.
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公开(公告)号：US11041395B2
公开(公告)日：2021-06-22
申请号：US16453101
申请日：2019-06-26
Applicant: United Technologies Corporation
Abstract: Methods for forming airfoils, core assemblies, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly configured to define one or more internal cavities of the airfoil body, the core assembly comprising at least core structure having a purge slot protrusion extending from a portion of the core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket.
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公开(公告)号：US10968753B1
公开(公告)日：2021-04-06
申请号：US16552450
申请日：2019-08-27
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Carey Clum , Timothy J. Jennings
Abstract: Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.
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公开(公告)号：US10801333B2
公开(公告)日：2020-10-13
申请号：US15954857
申请日：2018-04-17
Applicant: United Technologies Corporation
Inventor： Timothy J. Jennings , Tracy A. Propheter-Hinckley
Abstract: Methods for manufacturing airfoils of gas turbine engines are provided. The methods include forming a main body core, the main body core including a feed cavity core portion, the main body core configured to form at least a part of an airfoil including an airfoil body, a platform, and an attachment element, forming a platform circuit core having a platform core extension, wherein the platform circuit core is configured to form a cooling circuit in the platform, wherein at least one of the feed cavity core portion and the platform core extension includes a notch, assembling the platform circuit core to the main body core such that the platform core extension engages with the feed cavity core portion at the notch, casting an airfoil using the assembled platform circuit core and main body core, and removing a platform core extension element that is formed at the location of the notch.
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公开(公告)号：US10760432B2
公开(公告)日：2020-09-01
申请号：US15723461
申请日：2017-10-03
Applicant: United Technologies Corporation
Inventor： Carey Clum , Timothy J. Jennings
Abstract: Airfoils having a leading edge and a trailing edge, with a plurality of cavities therein including a leading edge hybrid cavity extending in a radial direction between a first end and a second end of the airfoil body along the leading edge. An airfoil side hybrid cavity is located toward the trailing edge relative to the leading edge hybrid cavity and positioned adjacent a side wall of the airfoil body. The airfoil side hybrid cavity extends in a radial direction between the first end and the second end and a divider rib extends radially between the first end and the second end along the side wall of the airfoil between the airfoil side hybrid cavity and the leading edge hybrid cavity. At least one first cross-over hole is formed within the divider rib to fluidly connect the airfoil side hybrid cavity to the leading edge hybrid cavity.
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Patent Agency Ranking
公开(公告)号：US20200080427A1
公开(公告)日：2020-03-12
申请号：US16129070
申请日：2018-09-12
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Timothy J. Jennings
Abstract: An airfoil according to an example of the present disclosure includes an airfoil section that extends in a radial direction from a platform to a tip, and extends in a thickness direction between a pressure side and a suction side that meet together at both a leading edge and a trailing edge. A purge partition radially divides the airfoil section. A perimeter of the purge partition follows along external walls of the airfoil section. The tip defines a tip pocket that extends radially inwardly from the tip to a floor. The airfoil section includes at least one internal cooling circuit and a purge cavity opposed to the at least one internal cooling circuit along the purge partition, with the purge partition bounded by the floor. The purge partition defines a first set of apertures that fluidly couple the at least one internal cooling circuit and the purge partition. A method of cooling a gas turbine engine component is also disclosed.
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公开(公告)号：US20190323361A1
公开(公告)日：2019-10-24
申请号：US15958080
申请日：2018-04-20
Applicant: United Technologies Corporation
Inventor： Timothy J. Jennings , Tracy A. Propheter-Hinckley
Abstract: A gas turbine engine article includes a blade that has a platform, and airfoil, and a root. The platform has a gaspath side and a non-gaspath side. The airfoil extends radially from the gaspath side of the platform and defines a leading end and a trailing end. The root is configured to secure the blade. The root extends radially from the non-gaspath side of the platform and defines forward and aft axial faces. There is an inlet orifice in the forward axial face. A cooling passage extends from the inlet orifice, through the root, and into the platform.
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公开(公告)号：US20190323360A1
公开(公告)日：2019-10-24
申请号：US15958056
申请日：2018-04-20
Applicant: United Technologies Corporation
Inventor： Timothy J. Jennings , Tracy A. Propheter-Hinckley
Abstract: A gas turbine engine article includes a blade that has a platform, an airfoil, and a root. The platform has a gaspath side and a non-gaspath side. The airfoil extends radially from the gaspath side and defines a leading end and a trailing end. The root is configured to secure the blade. The root extends radially from the non-gaspath side of the platform. The root defines forward and aft axial faces, and a radial channel in the aft axial face. The radial channel leads to an inlet orifice in the root. A cooling passage extends in the root from the inlet orifice.
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公开(公告)号：US20190309631A1
公开(公告)日：2019-10-10
申请号：US15945170
申请日：2018-04-04
Applicant: United Technologies Corporation
Inventor： Timothy J. Jennings , Tracy A. Propheter-Hinckley
IPC: F01D5/18
Abstract: Airfoils for gas turbine engines are provided. The airfoils include an internal cold wall defining a leading edge feed cavity proximate a leading edge and an external hot wall defining a leading edge cavity between an external wall and an internal wall. The leading edge cavity includes an inlet portion and an outlet portion. At least one impingement hole is formed in the internal wall and fluidly connects the leading edge feed cavity to the inlet portion. At least one film cooling hole is formed in the external wall and fluidly connects the outlet portion to an exterior of the airfoil body. The impingement inlet portion has a first height defined as a distance between the external wall and the internal wall for a length of the impingement inlet portion, and the film outlet portion has a second height that is greater than the first height.
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公开(公告)号：US10427075B2
公开(公告)日：2019-10-01
申请号：US15627809
申请日：2017-06-20
Applicant: United Technologies Corporation
Abstract: A gas turbine engine includes an engine static structure that provides a flow path. A metering hole is provided in the engine static structure. A strainer is arranged over the metering hole. The strainer includes multiple holes that have a total area that is greater than a metering hole area.
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