Gas turbine engine with twin offset gas generators

Patent metadata

Field	Value
Publication number	US-10094281-B2
Application number	US-201514595284-A
Country	US
Kind code	B2
Filing date	Jan 13, 2015
Priority date	Jan 30, 2014
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A gas turbine engine comprises a fan on an engine central axis. Plural gas generators are downstream of the fan, each along a respective central axis, mutually offset, and offset from the engine central axis. A fan drive turbine is on the engine central axis, downstream of the dual gas generators, and driven by output from the dual gas generators, to drive the fan.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a fan on an engine central axis;
plural gas generators downstream of the fan, each along a respective central axis that are mutually offset and non-parallel to the engine central axis and extend at a gas generator angle with respect to the engine central axis, wherein a gas generator forward end is closer to the engine central axis than a gas generator aft end; and
a fan drive turbine on the engine central axis, downstream of the plural gas generators, and driven by products of combustion downstream from the plural gas generators, for driving the fan;
wherein said plural gas generators each include a generator exhaust duct to deliver the products of combustion into an exhaust housing and across said fan drive turbine; and
said generator exhaust ducts extend at a generator exhaust duct angle relative to said engine central axis, wherein a generator exhaust duct aft end is closer to the engine central axis than a generator exhaust duct forward end, and
wherein the generator exhaust duct angle is greater than the gas generator angle.

2. The gas turbine engine as set forth in claim 1 , wherein said plural gas generators each include at least one compressor, a gas generator turbine and a combustor.

3. The gas turbine engine as set forth in claim 2 , wherein said fan drive turbine is driven by said products of combustion which have passed downstream through said gas generator turbines.

4. The gas turbine engine as set forth in claim 3 , wherein a nacelle surrounds said fan and receives bypass air for propulsion.

5. The gas turbine engine as set forth in claim 4 , wherein inlets into said plural gas generators are spaced circumferentially in a path of the bypass air delivered by said fan into said nacelle.

6. The gas turbine engine as set forth in claim 5 , wherein struts connect said nacelle to said exhaust housing.

7. The gas turbine engine as set forth in claim 5 , wherein there are two of said plural gas generators.

8. The gas turbine engine as set forth in claim 4 , wherein struts connect said nacelle to said exhaust housing.

9. The gas turbine engine as set forth in claim 1 , wherein a nacelle surrounds said fan and receives bypass air for propulsion.

10. The gas turbine engine as set forth in claim 9 , wherein inlets into said plural gas generators are spaced circumferentially in a path of the bypass air delivered by said fan into said nacelle.

11. The gas turbine engine as set forth in claim 1 , wherein a gear reduction mechanism is positioned between the fan drive turbine and the fan.

Assignees

• United Technologies Corp

Inventors

• Chandler Jesse M
• Suciu Gabriel L

Classifications

• F02C6/02 Primary

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

• F02K3/068

  being characterised by a short axial length relative to the diameter · CPC title

• F05D2250/314

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

• F02C6/06

  providing compressed gas (F02C6/10 takes precedence) · CPC title