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公开(公告)号：US20230043718A1
公开(公告)日：2023-02-09
申请号：US17882081
申请日：2022-08-05
Applicant: Raytheon Technologies Corporation
Inventor： Daniel P. Preuss , Dominic J. Mongillo, JR. , Jeremy B. Fredette , Robin Michael Patrick Prenter
IPC: F01D5/18
Abstract: A hollow airfoil body includes a baffle that is arranged in the airfoil body that extends in a radial direction and provides a fluid flow direction. The baffle has multiple holes that include first and second holes that are configured to conduct the cooling airflow in a chordwise direction toward the trailing edge of the airfoil body. The airfoil has a first standoff that extends from the airfoil body to support the baffle. The first axial standoff has a first length that defines an axial passage including the multiple holes. The airfoil includes a second standoff that has a second length less than the first length. The second standoff is arranged radially between the first and second holes. The first hole is smaller than the second hole. The second hole is downstream from the first hole relative to the fluid flow direction.
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公开(公告)号：US20230037659A1
公开(公告)日：2023-02-09
申请号：US17882114
申请日：2022-08-05
Applicant: Raytheon Technologies Corporation
Inventor： Daniel P. Preuss , Dominic J. Mongillo, JR. , Timothy J. Jennings
Abstract: A gas turbine engine includes a compressor section that provides first and second compressor stages that are configured to respectively provide first and second cooling fluids. The first compressor stage has a higher pressure than the second compressor stage. The gas turbine engine further includes a component that has platform with an internal cooling passage fed by first and second inlets that respectively receive fluid from the first and second cooling sources. The second inlet is downstream from the first inlet.
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公开(公告)号：US11225875B1
公开(公告)日：2022-01-18
申请号：US17159857
申请日：2021-01-27
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas J. Madonna , Kristopher K. Anderson , Justin M. Aniello , Jeffrey Michael Jacques , Daniel P. Preuss , Christina A. Ryan , Melissa Shallcross
Abstract: Vane assemblies are described. The vane assemblies include a platform, an airfoil extending from the platform, a forward rail extending from the platform and arranged along a forward side of the platform, and an aft rail extending from the platform and arranged along an aft side of the platform. At least one support beam is provided extending in a forward-aft direction between the forward rail and the aft rail and separated from the platform by a first distance. The at least one support beam has a thickness in a radial direction of 40% or less of a total radial extent from the platform to an outer diameter edge of at least one of the forward rail and the aft rail and the at least one support beam has a thickness in a circumferential direction of 30% or less of a total circumferential extent of vane assembly.
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公开(公告)号：US20200332667A1
公开(公告)日：2020-10-22
申请号：US16851720
申请日：2020-04-17
Applicant: Raytheon Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Daniel P. Preuss
IPC: F01D5/18
Abstract: Components for gas turbine engines are described. The components include an airfoil having a leading edge cavity with a baffle portion and a leading edge portion. A baffle is installed within the baffle portion and includes a first metering flow aperture. A first support element retention feature is located within the leading edge cavity. A first axial extending rib extends between an aft end of the cavity and a forward end proximate the first support element retention feature and is formed on an interior surface of the airfoil. A first axial extending flow channel extends along the first axial extending rib between an exterior surface of the baffle and an interior surface of the airfoil and the first metering flow aperture is located proximate the aft end of the first axial extending flow channel to generate a forward flowing cooling flow.
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