Offset cores for gas turbine engines

Patent metadata

Field	Value
Publication number	US-10415466-B2
Application number	US-201514921575-A
Country	US
Kind code	B2
Filing date	Oct 23, 2015
Priority date	Oct 27, 2014
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a propulsor including a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis (A), and a fan driven by the power turbine shaft, wherein the fan is aligned with the centerline axis and is defined forward of the power turbine;
a gas generator operatively connected to the propulsor, wherein the gas generator comprises a compressor and a combustor and the gas generator is located between the fan and the power turbine, the gas generator defining generator axis (B) offset from the centerline axis;
a fan case radially outward of the fan defining a fan inlet along the centerline axis (A), wherein the fan extends radially and radially traverses the gas generator in entirety and wherein the gas generator is in fluid communication with the fan inlet through a duct, wherein at least a portion of the duct is angled relative to the centerline axis and the generator axis (B);
a nacelle radially outward of the fan case, wherein the nacelle encloses the fan case and the gas generator; and
a transition duct defined between an exhaust outlet of the gas generator and an inlet of the power turbine for providing fluid communication therebetween, wherein the transition duct is angled relative to the centerline axis (A) and the generator axis (B).

2. A gas turbine engine as recited in claim 1 , wherein the generator axis (B) is substantially parallel to the centerline axis (A).

3. A gas turbine engine comprising:
a fan case defining a centerline axis (A), the fan case including a fan inlet;
a fan located within the fan case, the fan being driven by a power turbine operably coupled to the fan by a power turbine shaft, wherein the fan, the power turbine and the power turbine shaft are aligned with the centerline axis;
a gas generator comprising a compressor and a combustor, wherein the gas generator is located between the fan and the power turbine;
an outer core cowl radially inward of the fan case defining an axially extending splitter for dividing fluid flow entering at the fan inlet into a core gas path and a bypass flow path, wherein the core gas path includes a core inlet defined radially between the splitter and an inner core cowl;
a nacelle radially outward of the fan case, wherein the nacelle encloses the fan case and the gas generator, and wherein the fan extends radially and radially traverses the gas generator in entirety; and
the gas generator located entirely within the core gas path downstream of the core inlet, the gas generator defining a generator axis (B) that is offset from the centerline axis, wherein the entire gas generator is located radially inward from the outer core cowl.

4. The gas turbine engine as in claim 3 , further comprising a transition duct defined between an exhaust outlet of the gas generator and an inlet of the power turbine for providing fluid communication therebetween.

5. The gas turbine engine as in claim 4 , wherein the transition duct is angled relative to the centerline axis (A) and the generator axis (B).

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Hill James D

Classifications

• F05D2250/314

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

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F02C3/10

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

• F05D2240/24

  for turbines · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title