公开(公告)号：US20230304412A1

公开(公告)日：2023-09-28

申请号：US18161484

申请日：2023-01-30

Applicant: Raytheon Technologies Corporation

Inventor： Daniel P. Preuss ,  Dominic J. Mongillo, Jr. ,  Kristopher K. Anderson ,  Nicholas J. Madonna

IPC: F01D9/04 ,  F01D5/18 ,  F01D9/06

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D9/065 ,  F05D2240/121 ,  F05D2240/126 ,  F05D2240/81

Abstract: Vane assemblies for gas turbine engines are described. The vane assemblies include a platform having an interior platform surface, a forward rail, and an aft rail, wherein the interior platform surface, the forward rail, and the aft rail define a plenum, an airfoil extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity and a baffle installed within the leading edge cavity, and platform feed structure arranged on the platform in the plenum and defining a fluid path through the forward rail and into the baffle of the leading edge cavity.

公开(公告)号：US11828193B2

公开(公告)日：2023-11-28

申请号：US17307997

申请日：2021-05-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Nicholas J. Madonna ,  Daniel P. Preuss ,  Kristopher K. Anderson

IPC: F01D5/18 ,  F01D9/02 ,  F01D9/04 ,  F01D25/12 ,  B22C9/10 ,  B22C9/24 ,  F01D9/06

CPC classification number: F01D5/186 ,  B22C9/10 ,  B22C9/24 ,  F01D5/18 ,  F01D9/02 ,  F01D9/041 ,  F01D9/047 ,  F01D25/12 ,  F01D5/187 ,  F01D9/06 ,  F05D2260/202

Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.

公开(公告)号：US20210270138A1

公开(公告)日：2021-09-02

申请号：US17307997

申请日：2021-05-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Nicholas J. Madonna ,  Daniel P. Preuss ,  Kristopher K. Anderson

IPC: F01D5/18 ,  F01D9/02 ,  F01D9/04 ,  F01D25/12

Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.

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

IPC: F01D9/02 ,  F01D5/20 ,  F01D5/30 ,  F01D5/14

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.