Offset core engine architecture

Patent metadata

Field	Value
Publication number	US-10024235-B2
Application number	US-201514608227-A
Country	US
Kind code	B2
Filing date	Jan 29, 2015
Priority date	Mar 3, 2014
Publication date	Jul 17, 2018
Grant date	Jul 17, 2018

Abstract

A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a propulsion unit including a fan, and a free turbine connected through a fan shaft to drive said fan about a first axis;
a gas generating core, said gas generating core including at least a compressor, a combustion section, and a gas generating core turbine, wherein said compressor and said gas generating core turbine are configured to rotate about a second axis; and
an inlet duct configured to deliver air from said fan to said gas generating core, said inlet duct having a crescent shaped cross-section near said fan, which is curved about said fan shaft for a limited circumferential extent; and
wherein said first axis and second axis are non-parallel to each other.

2. The gas turbine engine as recited in claim 1 , wherein said free turbine is driven by said gas generating core.

3. The gas turbine engine as recited in claim 1 , wherein said inlet duct is positioned near a center of said fan.

4. The gas turbine engine as recited in claim 3 , wherein said inlet duct extends radially outwardly for less than 30% of a radial length of a vane of said fan.

5. The gas turbine engine as recited in claim 1 , wherein said crescent shaped cross-section defines a 180° arc.

6. The gas turbine engine as recited in claim 1 , further comprising a second gas generating core including at least a second compressor, a second combustion section, and a second gas generating core turbine, wherein said second compressor and said second gas generating core turbine are configured to rotate about a third axis.

7. The gas turbine engine as recited in claim 6 , wherein said second gas generating core includes a second inlet duct configured to deliver air from said fan to said second gas generating core, said second inlet duct having a crescent shaped cross-section near said fan.

8. The gas turbine engine as recited in claim 6 , wherein said third axis is non-parallel to said first axis or said second axis.

9. A gas turbine engine comprising:
a propulsion unit including a fan, and a free turbine connected through a fan shaft to drive said fan about a first axis;
a gas generating core including a compressor, a combustion section, and a gas generating core turbine, said gas generating core turbine connected to drive said compressor, and said compressor and said gas generating core turbine are configured to rotate about a second axis;
said first and second axes being non-parallel to each other;
said fan is configured to deliver a portion of the air it moves into an inlet duct positioned near a center of said fan, said inlet duct being configured to feed air into said gas generating core; and
wherein said inlet duct extends radially outwardly for less than 30% of a radial length of a vane of the fan section, said inlet duct being curved about said fan shaft over a limited circumferential extent.

10. The gas turbine engine as recited in claim 9 , said inlet duct having a crescent shaped cross-section near said fan.

11. The gas turbine engine as recited in claim 10 , wherein said crescent shaped cross-section defines a 180° arc.

12. The gas turbine engine as recited in claim 9 , further comprising a second gas generating core, said second gas generating core including a second compressor, a second combustion section and a second gas generating core turbine, said second gas generating core turbine connected to drive said second compressor, and said second compressor and said second gas generating core turbine are configured to rotate about a third axis.

13. The gas turbine engine as recited in claim 12 , further comprising a second inlet duct configured to feed air from near a center of said fan into said second gas generating core.

14. The gas turbine engine as recited in claim 13 , said second inlet duct having a crescent shaped cross-section near said fan.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Hill James D
• Chandler Jesse M

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F02C3/10

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

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F02K3/12 Primary

  characterised by having more than one gas turbine · CPC title

• F02C7/05

  having provisions for obviating the penetration of damaging objects or particles · CPC title