公开(公告)号：US20250012197A1

公开(公告)日：2025-01-09

申请号：US18348285

申请日：2023-07-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jason B. Husband ,  Canio Michael Hoffarth ,  Philip Andrew Varney

IPC: F01D11/00 ,  F02C7/28

Abstract: A gas turbine engine includes a rotor that has a seal surface and a shaft that is rotatable about an engine central axis. The shaft has an annular seal channel that opens to the seal surface. There is a seal for sealing against the seal surface. The seal has channels formed therein that define a tortuous seal wall with interconnected spring ligaments such that the seal is elastically diametrically expandable for installation clearance around the shaft and, once on the shaft, elastically diametrically collapsible into the annular seal channel.

公开(公告)号：US11181008B1

公开(公告)日：2021-11-23

申请号：US16931706

申请日：2020-07-17

Applicant: Raytheon Technologies Corporation

Inventor： Ulf J. Jonsson ,  Daniel L. Gysling ,  Philip Andrew Varney ,  Andrzej Ernest Kuczek

IPC: F16C27/04 ,  F16C19/06 ,  F01D25/16 ,  F16F15/023 ,  F16C35/04

Abstract: A fluid damping structure includes first and second annular elements, first and second inner seals, a first outer seal, a damping chamber, a supply plenum, a fill port, and a plurality of fluid passages. The first and second inner seals are disposed radially between and are engaged with the first annular element and the second annular element. The first outer seal forms a sealing interface between the first and second annular elements. The first outer seal is disposed radially outward from the first and second inner seals. The damping chamber is defined by the first and second annular elements and the first and second inner seals. The supply plenum is disposed contiguous with an axial side of the damping chamber and extends from the second inner seal to the first outer seal. The fill port is in fluid communication with the supply plenum and a source of damping fluid.

公开(公告)号：US20240385081A1

公开(公告)日：2024-11-21

申请号：US18198342

申请日：2023-05-17

Applicant: Raytheon Technologies Corporation

Inventor： Christopher T. Koetsch ,  Richard A. Lomenzo, JR. ,  Philip Andrew Varney

IPC: G01M15/14 ,  F01D21/00 ,  G01B21/16

Abstract: A system for determining rotor-dynamic orbit information including an engine case supporting at least one engine stage, each at least one engine stage including a rotor having blades; at least one blade tip sensor operatively coupled to the engine case and in operative communication with the blades; at least one compensation sensor in operative communication with the at least one blade tip sensor; and an orbit controller in operative communication with the at least one blade tip sensor and the at least one compensation sensor.