公开(公告)号：US11002149B2

公开(公告)日：2021-05-11

申请号：US16437501

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Ian J Bousfield ,  Duncan A MacDougall

IPC: F01D25/02 ,  F04D29/32 ,  F01D5/14

Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein the ratio of a maximum leading edge radius of the first rotor blades to a minimum leading edge radius of the first rotor blades is included between 2.2 and 3.5.

公开(公告)号：US10697374B1

公开(公告)日：2020-06-30

申请号：US16718405

申请日：2019-12-18

Applicant: ROLLS-ROYCE plc

Inventor： Ian J Bousfield

IPC: F02C7/36 ,  F02C7/057 ,  F02C3/06 ,  F02K3/06

Abstract: A gas turbine engine includes an inlet duct to guide a core engine flow to a compressor and an engine section stator arranged in the inlet duct upstream of the compressor including vanes with leading edges defining a first annulus area in the inlet duct, a mid-span leading edge point of the engine section stator vanes being arranged at a first radius. The compressor includes a first rotor with a row of first blades with leading edges defining a second annulus area; a mid-span leading edge point of the compressor first blades being arranged at a second radius and an axial distance from the engine section stator vane mid-span leading edge point. The ratio of the second to the first annulus area is equal or greater than 0.75, and the ratio of a difference between the first and second radius to the axial distance is equal or greater than 0.23.

公开(公告)号：US10578027B1

公开(公告)日：2020-03-03

申请号：US16411312

申请日：2019-05-14

Applicant: ROLLS-ROYCE PLC

Inventor： Duncan A MacDougall ,  Ian J Bousfield

IPC: F01D25/02 ,  F02C7/30

Abstract: A gas turbine engine includes a fan, compressor, combustor, and turbine coupled to the compressor through a shaft. The compressor includes first, second, and third stages with respective rotor blades and stator vanes. The rotor blades and stator vanes are arranged such that a sum of mid-span axial gaps between the trailing edge of the first rotor blades and the leading edge of the first stator vanes, the trailing edge of the first stator vanes and the leading edge of the second rotor blades, the trailing edge of the second rotor blades and the leading edge of the second stator vanes, and the trailing edge of the second stator vanes and the leading edge of the third rotor blades is equal to a × inlet ⁢ ⁢ flow ⁢ ⁢ function 10 . ⁢ a ≥ 75 ⁢ ⁢ mm ⁢ ⁢ and ⁢ ⁢ the ⁢ ⁢ inlet ⁢ ⁢ flow ⁢ ⁢ function = m ⁢ T P .