IP Library Granted Patent US 11,827,344
Granted Patent B2
US 11,827,344 · App. 17/116,726 · Granted Nov 28, 2023

Low noise ducted fan

Inventors: Alexander Dang Quang Truong (Dallas, TX); Karl Schroeder (Southlake, TX); Michael John Ryan (Colleyville, TX)
Assignee: Textron Innovations Inc.
B64C27/20B64C39/024B64D2033/0206B64U10/13B64U30/20B64U50/14
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Quick Facts
Patent No.
US 11,827,344
App. No.
17/116,726
Granted
Nov 28, 2023
Kind
B2
Abstract

An exemplary ducted fan includes a duct having a central longitudinal axis, a rotor hub and stator hub extending along the central longitudinal axis, rotor blades extending from the rotor hub, each of the rotor blades operable to rotate about its own pitch-change axis, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length, stators extending from the stator hub to an interior surface of the duct, each of the stators having a stator leading edge and a stator thickness, and a first separation between the rotor plane and the stator leading edge of not less than approximately 1.5 times the stator thickness.

Claims (27)

1. A ducted fan comprising:

a duct having a central longitudinal axis;

a rotor hub and a stator hub extending along the central longitudinal axis;

a plurality of rotor blades extending from the rotor hub, each of the plurality of rotor blades operable to rotate about a respective pitch-change axis of the rotor hub, the pitch-change axes lying in a rotor plane that is substantially perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length; and

a plurality of stators extending from the stator hub to an interior surface of the duct, each of the plurality of stators having a stator leading edge and a stator thickness;

wherein a first separation between the rotor plane and the stator leading edge is 1.5-2.7 times the stator thickness;

wherein a second separation between the rotor trailing edge and the stator leading edge is not less than the rotor chord length.

2. The ducted fan of claim 1 , wherein the first separation is substantially 1.5 times the stator thickness.

3. The ducted fan of claim 1 , wherein a number of the rotor blades and the stators is unequal.

4. The ducted fan of claim 1 , wherein a number of the rotor blades is greater than a number of the stators.

5. The ducted fan of claim 1 , wherein the stator leading edge is inclined toward the rotor plane extending from the stator hub to the interior surface of the duct.

6. The ducted fan of claim 1 , wherein the rotor trailing edge is inclined toward the rotor plane extending from the rotor hub toward the interior surface of the duct.

7. The ducted fan of claim 1 , wherein:

the stator leading edge is inclined toward the rotor plane extending from the stator hub to the interior surface of the duct; and

the rotor trailing edge is inclined toward the rotor plane extending from the rotor hub toward the interior surface of the duct.

8. The ducted fan of claim 1 , wherein the stator leading edge is inclined toward the rotor plane extending from the stator hub to the interior surface of the duct; and

the rotor trailing edge is inclined toward the rotor plane from the rotor hub toward the interior surface of the duct.

9. An aircraft comprising:

a fuselage having a forward portion and an aft portion; and

a tiltable ducted fan comprising:

a duct having a central longitudinal axis;

a rotor hub and a stator hub extending along the central longitudinal axis;

a plurality of rotor blades extending from the rotor hub, each of the plurality of rotor blades operable to rotate about a respective pitch-change axis of the rotor hub, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the plurality of rotor blades having a rotor trailing edge and a rotor chord length; and

a plurality of stators extending from the stator hub to an interior surface of the duct, each of the a plurality of stators having a stator leading edge and a stator thickness;

wherein a first separation between the rotor plane and the stator leading edge is 1.5-2.7 times the stator thickness;

wherein a second separation between the rotor trailing edge and the stator leading edge is not less than the rotor chord length.

10. The aircraft of claim 9 , wherein the stator leading edge is inclined toward the rotor plane extending from the stator hub to the interior surface of the duct.

Assignments (3)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Mar 16, 2021
From: BELL TEXTRON INC.
To: BELL TEXTRON RHODE ISLAND INC.
Reel/Frame 055602/0698 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Mar 16, 2021
From: BELL TEXTRON RHODE ISLAND INC.
To: TEXTRON INNOVATIONS INC.
Reel/Frame 055603/0134 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Dec 9, 2020
From: TRUONG, ALEXANDER DANG QUANG; SCHROEDER, KARL; RYAN, MICHAEL JOHN
To: BELL TEXTRON INC.
Reel/Frame 054597/0698 →
Continuity (1)
Related Publication 20220177121A1 · Jun 9, 2022
Cited By (1)
US 12,240,589