公开(公告)号：US11885235B2

公开(公告)日：2024-01-30

申请号：US17651179

申请日：2022-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Alex D. Wong ,  Yanhu Guo

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/22141

Abstract: An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

公开(公告)号：US20220025769A1

公开(公告)日：2022-01-27

申请号：US17498551

申请日：2021-10-11

Applicant: Raytheon Technologies Corporation

Inventor： Emma J. Place ,  Carlos Calixtro

IPC: F01D5/18

Abstract: A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.

公开(公告)号：US11781433B1

公开(公告)日：2023-10-10

申请号：US18077824

申请日：2022-12-08

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Yanhu Guo ,  Nelson D. Gonzalez

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2240/307 ,  F05D2250/74 ,  F05D2260/202

Abstract: A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. Further, the plurality of cooling holes are positioned at specific locations to improve film-cooling of the turbine blade while reducing negative impacts on performance of the turbine blade.

公开(公告)号：US11795826B2

公开(公告)日：2023-10-24

申请号：US17651174

申请日：2022-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Stephen D. Doll

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2220/323 ,  F05D2240/30

Abstract: A turbine blade for use in a gas turbine engine includes localized thickening of a neck pocket of the turbine blade to meet strength requirements while minimizing the weight of the turbine blade. More specifically, a convex spline is positioned within a suction side neck pocket of the turbine blade adjacent a leading edge of the neck pocket to increase the strength of the blade.

公开(公告)号：US20230258090A1

公开(公告)日：2023-08-17

申请号：US17651179

申请日：2022-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Alex D. Wong ,  Yanhu Guo

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2260/202

Abstract: An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

公开(公告)号：US20230258089A1

公开(公告)日：2023-08-17

申请号：US17651174

申请日：2022-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Stephen D. Doll

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2220/323 ,  F05D2240/30

Abstract: A turbine blade for use in a gas turbine engine includes localized thickening of a neck pocket of the turbine blade to meet strength requirements while minimizing the weight of the turbine blade. More specifically, a convex spline is positioned within a suction side neck pocket of the turbine blade adjacent a leading edge of the neck pocket to increase the strength of the blade.