公开(公告)号：US11459898B2

公开(公告)日：2022-10-04

申请号：US17245208

申请日：2021-04-30

Applicant: Raytheon Technologies Corporation

Inventor： Dominic J. Mongillo, Jr. ,  Atul Kohli ,  Jeffrey J. DeGray

IPC: F01D5/18 ,  F01D25/12

Abstract: Component for gas turbine engines are described. The components include a component wall having an inner wall surface and an outer wall surface and a cooling hole formed within the component wall. The cooling hole has an inlet formed in the inner wall surface and an outlet formed in the outer wall surface and defines a fluid path through the component wall. The cooling hole has a metering section extending from the inlet to a transition point and a diffusing section extending from the transition point to the outlet. The metering section is defined by a uniform geometry and the diffusing section is defined by a lobed portion that extends from the transition point toward the outlet. The lobed portion has a first lobe and a second lobe divided by a ridge surface and each lobe defines continuous curved surfaces along the length of the ridge surface.

公开(公告)号：US20220018260A1

公开(公告)日：2022-01-20

申请号：US17245208

申请日：2021-04-30

Applicant: Raytheon Technologies Corporation

Inventor： Dominic J. Mongillo, Jr. ,  Atul Kohli ,  Jeffrey J. DeGray

IPC: F01D5/18 ,  F01D25/12

Abstract: Component for gas turbine engines are described. The components include a component wall having an inner wall surface and an outer wall surface and a cooling hole formed within the component wall. The cooling hole has an inlet formed in the inner wall surface and an outlet formed in the outer wall surface and defines a fluid path through the component wall. The cooling hole has a metering section extending from the inlet to a transition point and a diffusing section extending from the transition point to the outlet. The metering section is defined by a uniform geometry and the diffusing section is defined by a lobed portion that extends from the transition point toward the outlet. The lobed portion has a first lobe and a second lobe divided by a ridge surface and each lobe defines continuous curved surfaces along the length of the ridge surface.

公开(公告)号：US11078793B2

公开(公告)日：2021-08-03

申请号：US16574359

申请日：2019-09-18

Applicant: Raytheon Technologies Corporation

Inventor： Wolfgang Balzer ,  Thomas J. Praisner ,  Atul Kohli ,  Mark F. Zelesky ,  Dominic J. Mongillo, Jr.

IPC: F01D5/14 ,  F01D5/02 ,  F01D5/18

Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.