-
公开(公告)号：US20230400062A1
公开(公告)日：2023-12-14
申请号：US18327507
申请日：2023-06-01
Applicant: ROLLS-ROYCE plc
Inventor： Craig TOWN , Jason J. MADGE
CPC classification number: F16C35/02 , F01D25/162 , F16C2360/23 , F05D2220/32
Abstract: A bearing carrier support for connecting a rotary shaft of a gas turbine engine to a static portion of the gas turbine engine. The bearing carrier support has: a bearing portion for supporting the rotary shaft; a flange portion for attaching the bearing carrier support to the static portion of the gas turbine engine; and a support portion that connects the flange portion and the bearing portion. The support portion has a plurality of circumferentially distributed struts that are axially aligned with respect to the rotary shaft. The number of struts is at least 500 and the diameter of each strut is no more than 3 mm.
-
公开(公告)号：US20230167767A1
公开(公告)日：2023-06-01
申请号：US17940035
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Benjamin J SELLERS , Jonathan A CHERRY , Craig TOWN
CPC classification number: F02C7/12 , F02C3/06 , F05D2220/323 , F05D2260/213 , F05D2260/40
Abstract: An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine positioned downstream of the fan assembly is rotationally connected to the turbine module. The fan assembly is in fluid communication with the compressor module by an intermediate duct and includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The compressor module includes a lowest pressure compressor stage having a row of rotor blades. An intermediate flow axis is defined joining a radially outer tip of a trailing edge of one of the fan blades of the highest pressure fan stage, and a radially outer tip of a leading edge of one of the rotor blades of a leading edge of a lowest-pressure compressor blade. An intermediate flow axis angle and the intermediate flow axis angle is from −20 to −30 degrees.
-
Search Results
2
records
(took 0.014 seconds)
