High pressure ratio gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsIan J Bousfield, Michael O Hales, Rory D Stieger
Life of this patent
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Abstract
A gas turbine engine including: a high pressure turbine, a low pressure turbine, a high pressure compressor coupled to the high pressure turbine by a high pressure shaft, a propulsor and a low pressure compressor coupled to the low pressure turbine via a low pressure shaft and a reduction gearbox; wherein the high pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages; and the high pressure compressor and low pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1.
Claims8
A gas turbine engine comprising:
- a high-pressure turbine;
- a low-pressure turbine;
- a high-pressure compressor coupled to the high-pressure turbine by a high-pressure shaft;
- and
- a propulsor and a low-pressure compressor coupled to the low-pressure turbine via a low-pressure shaft and a reduction gearbox,
- wherein the high-pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages,
- the high-pressure compressor and low-pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1,
- the low-pressure compressor consists of between 3 or 4 stages, the low-pressure compressor defines a cruise pressure ratio of between approximately 1.5 and 3.5, and
- wherein, when the high-pressure compressor comprises 10 stages, the average stage pressure ratio at cruise conditions is between 1.25 and 1.35 at a cruise pressure ratio of between 10:1 and 20:1, and when the high-pressure compressor comprises 11 stages, the average stage pressure ratio at cruise conditions is between 1.25 and 1.35 at a cruise pressure ratio of between 12:1 and 27:1.
Dependencies are inferred from the claim text.