公开(公告)号：US20250154906A1

公开(公告)日：2025-05-15

申请号：US18389075

申请日：2023-11-13

Applicant: RTX Corporation

Inventor： Jeffrey T. Morton ,  Andrew E. Breault

IPC: F02C7/36 ,  F02C7/32 ,  F16H57/00 ,  F16H57/02

Abstract: An assembly is provided for a turbine engine. This assembly includes an inner tower shaft, a layshaft, an outer tower shaft, an intermediate gear system, an inner gearbox and an outer gearbox. The layshaft is coupled to the inner tower shaft through an inner bevel gearing connection. The outer tower shaft is coupled to the layshaft through an outer bevel gearing connection. The intermediate gear system is configured to transfer mechanical power from the inner tower shaft to the layshaft and the outer tower shaft. The intermediate gear system includes the inner bevel gearing connection and the outer bevel gearing connection. The inner gearbox is coupled to the intermediate gear system through the layshaft. The outer gearbox is coupled to the intermediate gear system through the outer tower shaft.

公开(公告)号：US12018587B1

公开(公告)日：2024-06-25

申请号：US18480708

申请日：2023-10-04

Applicant: RTX CORPORATION

Inventor： Jeffrey T. Morton ,  Johan K. Westin ,  Jason B. Moran

IPC: F01D5/18 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202

Abstract: A turbine airfoil includes a body that has inner and outer platforms and an airfoil section that extends between the inner and outer platforms. Cooling holes define external breakout points from the body. The external breakout points are located in accordance with Cartesian coordinates of at least points 1 through 11, 193 through 201, and 268 through 275 set forth in Table 1 herein.

公开(公告)号：US12203385B1

公开(公告)日：2025-01-21

申请号：US18431050

申请日：2024-02-02

Applicant: RTX Corporation

Inventor： Jeffrey T. Morton ,  Stephen G. Pixton

IPC: F01D5/14

Abstract: An assembly for an aircraft propulsion system includes a propulsor rotor and a guide vane structure. The propulsor rotor is configured to rotate about an axis. The guide vane structure includes a plurality of guide vanes arranged circumferentially about the axis. The guide vane structure is axially next to and downstream of the propulsor rotor. The guide vanes include a first guide vane. The first guide vane includes a camber line, a leading edge, a trailing edge, a leading edge section and a trailing edge section. The first guide vane extends longitudinally along the camber line from the leading edge to the trailing edge. The leading edge section forms the leading edge. The trailing edge section forms the trailing edge. The leading edge section is configured to move longitudinally along the camber line relative to the trailing edge section to change a camber of the first guide vane.