Gas turbine engine inlet wall design

Patent metadata

Field	Value
Publication number	US-10907544-B2
Application number	US-201514665081-A
Country	US
Kind code	B2
Filing date	Mar 23, 2015
Priority date	Mar 27, 2014
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
an inlet duct formed with a generally elliptical shape including a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct, wherein the inlet duct includes a vertical centerline and the first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections and the area of the second set of ellipse sections increases toward a downstream end of the inlet duct; and
a fan section having an axis of rotation, wherein the axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice and the inlet duct is upstream of the fan section.

2. The gas turbine engine of claim 1 , wherein the axis of rotation is spaced a first distance from the vertical centerline at the throat of the inlet duct and the axis of rotation is spaced a second distance from the vertical centerline at an intermediate location along the inlet duct, wherein the first distance is greater than the second distance.

3. The gas turbine engine of claim 2 , wherein the axis of rotation is spaced a third distance from the vertical centerline at an axial location adjacent the fan section, the third distance is less than the second distance.

4. The gas turbine engine of claim 1 , wherein the axis of rotation is spaced a first distance from the vertical centerline at a first axial position in the inlet duct and the axis of rotation is spaced a second distance from the vertical centerline at a second axial position in the inlet duct, the first distance is greater than the second distance.

5. The gas turbine engine of claim 4 , wherein the first axial position is upstream of the second axial position.

6. The gas turbine engine of claim 1 , wherein the axis of rotation is spaced from the vertical centerline in a direction of rotation of an upper fan blade of the fan section.

7. The gas turbine engine of claim 2 , wherein the vertical centerline follows a curvilinear profile relative to the axis of rotation upstream of the fan section and the axis of rotation intersects an upstream most end of the first set ellipse sections in the upper portion of the inlet duct and spaced from the vertical centerline.

8. The gas turbine engine of claim 1 , wherein the vertical centerline intersects the axis of rotation at a downstream location of the inlet duct adjacent the fan section.

9. The gas turbine engine of claim 1 , wherein the throat of the inlet duct at least partially defines the generally elliptical shape and the vertical centerline extends through the generally elliptical shape at least partially defined by the throat.

10. The gas turbine engine of claim 1 , wherein the fan section is a single fan section and the inlet duct is upstream of the fan section.

11. The gas turbine engine of claim 1 , wherein the throat of the inlet duct includes a first vertical dimension and the inlet duct includes a second vertical dimension downstream of the throat adjacent the fan section and the second vertical dimension is greater than the first vertical dimension.

12. The gas turbine engine of claim 1 , wherein a vertical component of the second set of ellipse sections increases toward the downstream end of the inlet duct and a horizontal component of the second set of ellipse sections decreases toward the downstream end of the inlet duct and the inlet duct includes a circular cross-section immediately upstream of the fan section.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Voytovych Dmytro Mykolayovych
• Sharma Om P

Classifications

• B64D2033/0253

  specially adapted for particular type of aircraft · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• B64C2039/105

  of blended wing body type · CPC title

• F05D2250/312

  the axes being parallel to each other · CPC title

• F05D2250/14

  elliptical · CPC title