US 2026/0054843 A1Published application

Aircraft with an unducted fan propulsor

AssigneeGeneral Electric Company

InventorsSara Elizabeth Carle, Daniel L. Tweedt, Syed Arif Khalid, Andrew Breeze-Stringfellow, William Bowden, Trevor H. Wood, Kishore Ramakrishnan

Life of this patent

Estimating the term…

Abstract

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

Claims20

Dependent claims

An aircraft comprising:

a fuselage;
a pair of wings extending from the fuselage,
two or more unducted fan propulsors, each of the unducted fan propulsors mounted relative to one of the wings on a high pressure side thereof, the respective unducted fan propulsor having a centerline (CL), a plurality of blades arranged in a forward array and a plurality of blades arranged in a rearward array, wherein only one of the forward and rearward array of blades are rotating blades and the rotating blades define a maximum outer diameter (D), and wherein another of the forward and rearward array of blades are nonrotating blades including an outlet guide vane, the outlet guide vane including a hub portion, a tip portion, and a peak positioned between the hub portion and the tip portion in a radial direction defined by the respective unducted fan propulsor, the hub portion including a forward sweep, the tip portion including an aft sweep, wherein the outlet guide vane includes a first chord length in the tip portion, wherein the outlet guide vane includes a second chord length, and wherein a ratio of the first chord length to the second chord length is less than 0.8;
a point (P) located at an intersection of the CL and a line HP perpendicular to the CL that passes through an axial midpoint between a rearward trailing edge at a root of a blade of the rearward array and a forward leading edge at a root of a blade of the forward array when the forward leading edge and rearward trailing edge of the respective blades are aligned with each other;
an airfoil section having an effective quarter chord point QC;
and
a positioning line (R) having a length (RL) and extending from the QC to the point P of the unducted fan propulsor at an angle θ measured positive in a counter-clockwise direction when the high pressure side of the airfoil section is below the airfoil section when viewed looking from an outboard position towards an inboard position of the wing;
wherein 0.07≤RL/D≤2.0 and θ is between 187° and 342°.

5 more elements

An aircraft, comprising:

a fuselage;
an airfoil extending from the fuselage, the airfoil having an airfoil section defining an effective quarter chord point (QC);
an unducted fan propulsor mounted relative to the airfoil section on a high pressure side thereof, the unducted fan propulsor having a centerline (CL), a plurality of blades arranged in a forward array and a plurality of blades arranged in a rearward array, wherein only one of the forward and rearward array of blades are rotating blades and the rotating blades define a maximum outer diameter (D), and wherein another of the forward and rearward array of blades are nonrotating blades including an outlet guide vane, the outlet guide vane including a hub portion, a tip portion, and a peak positioned between the hub portion and the tip portion in a radial direction defined by the unducted fan propulsor, the hub portion including a forward sweep, the tip portion including an aft sweep, wherein the outlet guide vane includes a first chord length in the tip portion, wherein the outlet guide vane includes a second chord length, and wherein a ratio of the first chord length to the second chord length is less than 0.8;
a point (P) located at an intersection of the CL and a line HP perpendicular to the CL that passes through an axial midpoint between a rearward trailing edge at a root of a blade of the rearward array and a forward leading edge at a root of a blade of the forward array when the forward leading edge and rearward trailing edge of the respective blades are aligned with each other;
and
an ellipse origin positioning line (EOR) having a length (EORL) extending from the QC to an ellipse origin (OR) at an angle θ measured positive in a counter-clockwise direction when the high pressure side of the airfoil section is below the airfoil section, and measured positive in a clockwise direction when the high pressure side of the airfoil section is above the airfoil section, when viewed looking for an outboard position towards an inboard position;
wherein the P of the unducted fan propulsor is located within a first ellipse having a first major axis length (1MajAL) and a first minor axis length (1MinAL) with a first ellipse origin defined by EORL/D of 0.938 and θ of 253.6°, and where 1MajAL/D is 2.8 and 1MinAL/D is 1.7.

4 more elements

An aircraft, comprising:

a fuselage;
an airfoil extending from the fuselage, the airfoil having an airfoil section defining an effective quarter-chord point (QC);
an unducted fan propulsor mounted relative to the airfoil section on a high pressure side thereof, the unducted fan propulsor having a centerline (CL), a plurality of blades arranged in a forward array and a plurality of blades arranged in a rearward array, wherein one of the forward and rearward array of blades are rotating blades and the rotating blades define a maximum outer diameter (D), and wherein another of the forward and rearward array of blades are nonrotating blades including an outlet guide vane, the outlet guide vane including a hub portion, a tip portion, and a peak positioned between the hub portion and the tip portion in a radial direction defined by the unducted fan propulsor, the hub portion including a forward sweep, the tip portion including an aft sweep, wherein the outlet guide vane includes a first chord length in the tip portion, wherein the outlet guide vane includes a second chord length, and wherein a ratio of the first chord length to the second chord length is less than 0.8;
a point (P) located at an intersection of the CL and a line HP perpendicular to the CL that passes through an axial midpoint between a rearward trailing edge at a root of a blade of the rearward array and a forward leading edge at a root of a blade of the forward array when the forward leading edge and rearward trailing edge of the respective blades are aligned with each other;
and
a positioning line (R) having a length (RL) and extending from the QC to the point P of the unducted fan propulsor at an angle θ measured positive in a counter-clockwise direction when the high pressure side of the airfoil section is below the airfoil section, and measured positive in a clockwise direction when the high pressure side of the airfoil section is above the airfoil section, when viewed looking from an outboard position towards an inboard position (e.g. the fuselage) OR when viewed with the LE to the left of the TE;
wherein 0.065<RL/D<1.98 and θ is between 187° and 340°;
and wherein RL/D and θ of the P of the unducted fan propulsor adhere to the following expressions:
R
⁢
L
D
⁢
(
(
1.4161
*
[
1
.
8
⁢
8
⁢
9
⁢
7
⁢
8
*
sin
2
⁢
(
θ
)
-
0
.
0
⁢
8
⁢
7
⁢
5
*
cos
2
⁢
(
θ
)
+
0.477
*
sin
⁢
(
θ
)
*
cos
⁢
(
θ
)
]
+
1.764
*
sin
⁢
(
θ
)
+
0.19146
*
cos
⁢
(
θ
)
)
1.96
*
sin
2
⁢
(
θ
)
+
0
.
7
⁢
2
⁢
2
⁢
5
*
cos
2
⁢
(
θ
)
>
0
and
R
⁢
L
D
⁢
(
(
1.4161
*
[
1
.
8
⁢
8
⁢
9
⁢
7
⁢
8
*
sin
2
⁢
(
θ
)
-
0
.
0
⁢
8
⁢
7
⁢
5
*
cos
2
⁢
(
θ
)
+
0.477
*
sin
⁢
(
θ
)
*
cos
⁢
(
θ
)
]
+
1.764
*
sin
⁢
(
θ
)
+
0.19146
*
cos
⁢
(
θ
)
)
1.96
*
sin
2
⁢
(
θ
)
+
0
.
7
⁢
2
⁢
2
⁢
5
*
cos
2
⁢
(
θ
)
<
0

214 more elements

Dependencies are inferred from the claim text.

Facts

Application: 19/371,634Filed 28 Oct 2025
Priority: 4 Aug 2023
Published: 26 Feb 2026
Term ends: Not estimatedThe source records don’t support an estimate.

Classification19 codes

B64C 3/32
Wings: specially adapted for mounting power plant
B64D 27/18
Of jet type: within, or attached to, wings
B64C 11/48
Arrangements of, or constructional features peculiar to, multiple propellers: units of two or more coaxial propellers
B64D 27/402
Arrangements for mounting power plants in aircraft: comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant

Family

Application18/230,609Continuation in part · filed 4 Aug 2023
Application18/652,052Continuation in part · filed 1 May 2024
Application19/371,634Continuation in part
US 12,365,471 B2Related patent
US 12,384,522 B2Related patent
US 2025/0042537 A1Published application
US 2025/0042558 A1Published application
US 2026/0054843 A1This patent

From the US filing history. Foreign family members aren’t listed.

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Abstract

An aircraft comprising:

a fuselage;
a pair of wings extending from the fuselage,
two or more unducted fan propulsors, each of the unducted fan propulsors mounted relative to one of the wings on a high pressure side thereof, the respective unducted fan propulsor having a centerline (CL), a plurality of blades arranged in a forward array and a plurality of blades arranged in a rearward array, wherein only one of the forward and rearward array of blades are rotating blades and the rotating blades define a maximum outer diameter (D), and wherein another of the forward and rearward array of blades are nonrotating blades including an outlet guide vane, the outlet guide vane including a hub portion, a tip portion, and a peak positioned between the hub portion and the tip portion in a radial direction defined by the respective unducted fan propulsor, the hub portion including a forward sweep, the tip portion including an aft sweep, wherein the outlet guide vane includes a first chord length in the tip portion, wherein the outlet guide vane includes a second chord length, and wherein a ratio of the first chord length to the second chord length is less than 0.8;
a point (P) located at an intersection of the CL and a line HP perpendicular to the CL that passes through an axial midpoint between a rearward trailing edge at a root of a blade of the rearward array and a forward leading edge at a root of a blade of the forward array when the forward leading edge and rearward trailing edge of the respective blades are aligned with each other;
an airfoil section having an effective quarter chord point QC;
and
a positioning line (R) having a length (RL) and extending from the QC to the point P of the unducted fan propulsor at an angle θ measured positive in a counter-clockwise direction when the high pressure side of the airfoil section is below the airfoil section when viewed looking from an outboard position towards an inboard position of the wing;
wherein 0.07≤RL/D≤2.0 and θ is between 187° and 342°.

5 more elements

Facts

Application

19/371,634Filed 28 Oct 2025

Priority

4 Aug 2023

Published

26 Feb 2026

Term ends

Not estimatedThe source records don’t support an estimate.

Classification19 codes

B64C 3/32
Wings: specially adapted for mounting power plant
B64D 27/18
Of jet type: within, or attached to, wings
B64C 11/48
Arrangements of, or constructional features peculiar to, multiple propellers: units of two or more coaxial propellers
B64D 27/402
Arrangements for mounting power plants in aircraft: comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant

Family

Application18/230,609Continuation in part · filed 4 Aug 2023

Application18/652,052Continuation in part · filed 1 May 2024

Application19/371,634Continuation in part

US 12,365,471 B2Related patent

US 12,384,522 B2Related patent

US 2025/0042537 A1Published application

US 2025/0042558 A1Published application

US 2026/0054843 A1This patent

From the US filing history. Foreign family members aren’t listed.