公开(公告)号：US10760530B2

公开(公告)日：2020-09-01

申请号：US16423541

申请日：2019-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton ,  Michael C Willmot

IPC: F02K3/06 ,  F02C3/04 ,  F02C7/36 ,  F02C7/04 ,  B64D33/02 ,  B64D27/12

Abstract: A gas turbine engine for an aircraft including: engine core including a turbine; and fan including a plurality of fan blades extending radially from a hub, each fan blade having a leading and trailing edge. Turbine includes a lowest pressure turbine stage having a row of rotor blades each extending radially and having a leading and trailing edge. A fan-turbine radius difference is measured as radial distance between: a point on a circle swept by a radially outer tip of the trailing edge of each of the rotor blades of the lowest pressure stage of the turbine; and a point on a circle swept by a radially outer tip of the leading edge of each of fan blades; and a fan speed to fan-turbine radius ratio defined as: the ⁢ ⁢ maximum ⁢ ⁢ take ⁢ - ⁢ off ⁢ ⁢ rotational ⁢ ⁢ speed ⁢ ⁢ of ⁢ ⁢ the ⁢ ⁢ fan fan ⁢ - ⁢ turbine ⁢ ⁢ radius ⁢ ⁢ difference ⁢ ⁢ ( 120 ) is in a range between 0.8 rpm/mm to 5 rpm/mm.

公开(公告)号：US10648475B1

公开(公告)日：2020-05-12

申请号：US16671215

申请日：2019-11-01

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton ,  Michael C Willmot

IPC: F01D1/02 ,  F01D1/04 ,  F04D19/00 ,  F01D5/12

Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, compressor, and core shaft connecting turbine to compressor; a fan located upstream of the engine core and including a plurality of fan blades each having a leading and trailing edge. The turbine includes a lowest pressure turbine stage having a row of rotor blades, each rotor blades extending radially and having a leading and trailing edge. The engine has a fan tip axis that joins a radially outer tip of the leading edge of a fan blade and the radially outer tip of the trailing edge of a rotor blade of the lowest pressure stage. The fan tip axis lies in a longitudinal plane which contains a centreline of engine. A fan axis angle is defined as the angle between fan tip axis and centreline, and is in a range between 10 and 20 degrees.

公开(公告)号：US10583932B1

公开(公告)日：2020-03-10

申请号：US16398909

申请日：2019-04-30

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton ,  Michael C Willmot

IPC: F02C7/04 ,  B64D33/02 ,  B64D27/12 ,  F02K3/06

Abstract: A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio is: the ⁢ ⁢ turbine ⁢ ⁢ diameter ⁢ ⁢ at ⁢ ⁢ an ⁢ ⁢ axial location ⁢ ⁢ of ⁢ ⁢ the ⁢ ⁢ lowest ⁢ ⁢ pressure ⁢ ⁢ rotor ⁢ ⁢ stage ⁢ ground ⁢ ⁢ plane ⁢ ⁢ to ⁢ ⁢ wing ⁢ ⁢ distance and a quasi-non-dimensional mass flow rate Q defined as: Q = W ⁢ T ⁢ ⁢ 0 P ⁢ ⁢ 0 · A flow where: W is mass flow rate through the fan in Kg/s; T0 is average stagnation temperature of the air at the fan face in Kelvin; P0 is average stagnation pressure of the air at the fan face in Pa; and Aflow is the flow area of the fan face in m2, and wherein a Q ratio of: the downstream blockage ratio×Q is in a range from 0.005 to 0.01.

公开(公告)号：US12012216B2

公开(公告)日：2024-06-18

申请号：US18061330

申请日：2022-12-02

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton

IPC: B64D27/40 ,  B64D27/10 ,  F02C7/20

CPC classification number: B64D27/40 ,  B64D27/10 ,  B64D27/406 ,  F02C7/20 ,  F05D2220/323 ,  F05D2240/90

Abstract: A gas turbine engine includes a support structure for attaching the engine to an aircraft pylon. The support structure includes: an engine-side interface member, a pylon-side interface member interfacing to the engine-side interface member, and a top V-shaped connection formation above the engine core and pair of side V-shaped connection formations on opposite lateral sides of the engine core, each V-shaped connection formation being formed by a pair of connection members meeting at a vertex, the vertex of the top V-shaped connection formation joining to the top of the engine-side interface member, the vertices of the side V-shaped connection formations respectively joining to the bottom ends of the engine-side interface member, and the connection members extending forwardly from their respective vertices to join to front fixation points at the core casing.

公开(公告)号：US11053947B2

公开(公告)日：2021-07-06

申请号：US16825361

申请日：2020-03-20

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton ,  Michael C Willmot

IPC: F04D19/00 ,  F01D5/12

Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, compressor, and core shaft connecting turbine to compressor; a fan located upstream of the engine core and including a plurality of fan blades each having a leading and trailing edge. The turbine includes a lowest pressure turbine stage having a row of rotor blades, each rotor blades extending radially and having a leading and trailing edge. The engine has a fan tip axis that joins a radially outer tip of the leading edge of a fan blade and the radially outer tip of the trailing edge of a rotor blade of the lowest pressure stage. The fan tip axis lies in a longitudinal plane which contains a centreline of engine. A fan axis angle is defined as the angle between fan tip axis and centreline, and is in a range between 10 and 20 degrees.