公开(公告)号：US20210222630A1

公开(公告)日：2021-07-22

申请号：US17061002

申请日：2020-10-01

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE CORPORATION ,  ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Inventor： Mark D. TAYLOR ,  Erik JANKE ,  Rory D. STIEGER ,  Daniel SWAIN

IPC: F02C7/36 ,  F02C3/10

Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator turbine is a single stage turbine having a specific work of from 200 to 350 kilojoules per kilogram, said specific work being the power output of the turbine per unit mass flow therethrough.

公开(公告)号：US20210123387A1

公开(公告)日：2021-04-29

申请号：US17061046

申请日：2020-10-01

Applicant: ROLLS-ROYCE plc

Inventor： Rory D. STIEGER ,  Mark D. TAYLOR

IPC: F02C7/36 ,  F01D15/10

Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The rotational speeds of the turbines are dependent upon an outlet temperature of the combustor, and a speed relationship between the turbines is defined as the ratio of rotational speeds of the turbines over a running range of non-dimensional power outputs of the gas turbine engine. A first derivative of the speed relationship is from 0.9 to 1.1

公开(公告)号：US20210122488A1

公开(公告)日：2021-04-29

申请号：US17061079

申请日：2020-10-01

Applicant: ROLLS-ROYCE PLC ,  ROLLS-ROYCE CORPORATION

Inventor： Daniel SWAIN ,  Rory D. STIEGER ,  Mark D. TAYLOR

IPC: B64D41/00 ,  B64D27/10 ,  F02C3/08 ,  F02C6/00 ,  H02K11/33

Abstract: An auxiliary power unit (10) for an aircraft (1) comprises a gas turbine engine comprising an engine core (12). The engine core comprises a core compressor (14) and core turbine (18) coupled by a core shaft (24). The auxiliary power unit further comprises a load spool comprising a load compressor (30), a load turbine (20) and a permanent magnet electric machine (28), each being coupled by a load shaft (26). The load shaft (26) and core shaft (24) are configured to rotate independently of one another.

公开(公告)号：US20210222617A1

公开(公告)日：2021-07-22

申请号：US17060986

申请日：2020-10-01

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Inventor： Rory D. STIEGER ,  Mark D. TAYLOR ,  Erik JANKE

IPC: F02C3/10 ,  F02C7/36

Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The expansion ratios of the turbines are dependent upon an outlet temperature of the combustor, and an expansion relationship between the turbines is defined as the ratio of expansion ratios of the turbines over a running range of non-dimensional power outputs of the gas turbine engine. A second derivative of the expansion relationship is from 0.6 to 1.0.