Gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsRory D. Stieger, Daniel Swain
Life of this patent
Estimating the term…
Abstract
A 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 compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.
Claims10
A gas turbine engine comprising, in fluid flow series:
- a gas-generator compressor;
- a combustor,
- a single stage gas-generator turbine, which comprises an uncooled, subsonic throughflow rotor and a supersonic throughflow stator;
- and
- a free power turbine,
- wherein the gas-generator turbine has a specific work of from 200 to 350 kilojoules per kilogram, the specific work being the power output of the gas-generator turbine per unit mass flow therethrough,
- the gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage,
- an International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and
- a ratio of ISA SLS pressure rise across the axial compression stages to ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.
Dependencies are inferred from the claim text.