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US 9,869,248 B2Granted
Two spool gas generator to create family of gas turbine engines
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Brian D. Merry
Life of this patent
Estimating the term…
Abstract
A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator.
Claims9
A family of gas turbine engines comprising:
- substantially mutually alike gas generators;
- a plurality of propulsor turbines each driven by products of combustion downstream of one of the gas generators, with at least one of the plurality of propulsor turbines driving a fan and another of the plurality of propulsor turbines driving a propeller;
- wherein said gas generators each have a compressor section with a first and a second compressor rotor, and a turbine section with a first and second turbine rotor, and the propulsor turbine is downstream of the second turbine rotor;
- and
- wherein said second compressor rotor having a first overall pressure ratio, and said first compressor rotor having a second overall pressure ratio, with a ratio of said first overall pressure ratio to said second overall pressure ratio being greater than or equal to about 2.0.
2 more elements
A gas turbine engine comprising:
- a first shaft connecting a first compressor rotor to be driven by a first turbine rotor;
- a second shaft connecting a second compressor rotor to be driven by a second turbine rotor, with said second compressor rotor being upstream of the first compressor rotor, and said first turbine rotor being upstream of said second turbine rotor, said second compressor rotor having a first overall pressure ratio, and said first compressor rotor having a second overall pressure ratio, with a ratio of said first overall pressure ratio to said second overall pressure ratio being greater than or equal to about 2.0;
- a propulsor turbine operatively connected to drive a propeller through a third shaft, with said propulsor turbine being positioned to be downstream of said first turbine rotor;
- and
- a mid-turbine frame including a bearing supporting a downstream end of said first shaft, said mid-turbine frame being positioned intermediate said second turbine rotor, and said propulsor turbine, with an intermediate case including a bearing supporting each of said first and second shafts, and an inlet case being positioned upstream of said second compressor rotor, and including a bearing supporting said first shaft, and a turbine exhaust case receiving said propulsor turbine, and further including bearings supporting said third shaft.
2 more elements
Dependencies are inferred from the claim text.