Two spool gas generator to create family of gas turbine engines

Patent metadata

Field	Value
Publication number	US-9869248-B2
Application number	US-201314647537-A
Country	US
Kind code	B2
Filing date	May 29, 2013
Priority date	Dec 17, 2012
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

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.

First claim

The invention claimed is:

1. 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. The family of gas turbine engines as set forth in claim 1 , wherein said high pressure turbine includes a single turbine stage.

3. The family of gas turbine engines as set forth in claim 2 , wherein said low pressure compressor rotor includes eight stages.

4. The family of gas turbine engines as set forth in claim 3 , wherein said first compressor rotor includes six stages.

5. The family of gas turbine engines as set forth in claim 1 , wherein said propulsor turbine driving a fan located at an upstream end to supply a free airstream to said second compressor rotor.

6. The family of gas turbine engines as set forth in claim 5 , wherein said fan rotating about a first axis, and said first and second compressor rotors, and said first and second turbine rotors rotating about a second axis, and said first and second axes being non-parallel.

7. The family of gas turbine engines as set forth in claim 1 , wherein said propulsor turbine driving a plurality of propellers.

8. 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.

9. The family of gas turbine engines as set forth in claim 1 , wherein when said propulsor turbine drives said fan, said gas generator is a reverse flow gas generator with said compressor section spaced further into the engine than is said turbine section, and with said propulsor turbine further outward of said turbine section such that air heading to said compressor section initially passes past said propulsor turbine, said turbine section, and then is delivered into said compressor section.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Merry Brian D

Classifications

• F02C6/02 Primary

  Plural gas-turbine plants having a common power output · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title

• F05D2250/31

  according to the direction of their main axis or their axis of rotation · CPC title

• F02K3/06

  with front fan · CPC title

• F05D2220/324

  to drive unshrouded, low solidity propeller · CPC title