US 2026/0036136 A1Published application

Turbomachine and method of assembly

OwnerJixian Yao, Trevor H. Wood +4inventors

InventorsJixian Yao, Trevor H. Wood, Kishore Ramakrishnan, William J. Solomon, Giridhar Jothiprasad, Aaron J. King

Life of this patent

Estimating the term…

Abstract

A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.

Claims20

Dependent claims

A turbomachine for an aircraft comprising:

an annular casing;
and
a fan disposed inside the annular casing and mounted for rotation about an axial centerline, the fan including fan blades that extend radially outwardly toward the annular casing, a fan blade including:
an airfoil extending outwardly from a sloped root and including opposite pressure and suction sides extending longitudinally in span from the sloped root to an opposite tip, and extending axially in chord between opposite leading and trailing edges,
the airfoil further including stagger increasing between the sloped root and tip, camber decreasing therebetween, and chord length increasing outboard from the sloped root to barrel the airfoil along both the leading and trailing edges,
the airfoil further including maximum forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between a maximum barrel in the airfoil and the sloped root;
wherein the fan includes an average fan chord width of the fan blades (“c”), a diameter of the fan (“D”), a fan pressure ratio (“FPR”), and a redline corrected fan tip Mach number
(
“
M
tip
,
c
(
R
⁢
L
)
”
)
according to a First Performance Factor (“FPF”),
wherein
FPF
=
[
c
0.15
·
D
]
⁢
/
[
[
FPR
-
1
0.4
]
/
M
tip
,
c
(
R
⁢
L
)
]
-
1.23
,
wherein
⁢
m
1
·
[
M
tip
,
c
(
R
⁢
L
)
-
1
.
1
]
+
9
.14
>
FPF
>
m
2
·
[
M
tip
,
c
(
R
⁢
L
)
-
1
.
1
]
,
and
wherein m1 is equal to 9.43 when
M
tip
,
c
(
RL
)
is greater than or equal to 1.1 and is equal to 27.02 when
M
tip
,
c
(
RL
)
is less than 1.1, and
wherein m2 is equal to 0.87 when
M
tip
,
c
(
RL
)
is greater than or equal to 1.1 and is equal to 3.34 when
M
tip
,
c
(
RL
)
is less than 1.1.

130 more elements

A turbomachine comprising for an aircraft comprising:

an annular casing;
and
a fan disposed inside the annular casing and mounted for rotation about an axial centerline, the fan including fan blades that extend radially outwardly toward the annular casing, a fan blade including:
an airfoil extending outwardly from a sloped root and including opposite pressure and suction sides extending longitudinally in span from the sloped root to an opposite tip, and extending axially in chord between opposite leading and trailing edges,
the airfoil further including stagger increasing between the sloped root and tip, camber decreasing therebetween, and chord length increasing outboard from the sloped root to barrel the airfoil along both the leading and trailing edges,
the airfoil further including maximum forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between a maximum barrel in the airfoil and the sloped root;
wherein the fan includes a fan hub-to-tip ratio (“HTR”), a fan blade count (“BC”), a fan pressure ratio (“FPR”), and a redline corrected fan tip Mach number
(
“
M
tip
,
c
(
R
⁢
L
)
”
)
according to a Second Performance Factor (“SPF”),
wherein
SPF
=
π
4
⁢
(
1
-
HTR
2
)
/
(
B
⁢
C
2
⁢
0
)
/
(
FPR
-
1
0.4
)
/
M
tip
,
c
(
RL
)
-
0.97
,
wherein
⁢
m
3
·
[
M
tip
,
c
(
R
⁢
L
)
-
1
.
1
]
+
2
.52
>
SPF
>
m
4
·
[
M
tip
,
c
(
R
⁢
L
)
-
1
.1
]
wherein m3 is equal to 3.17, and
wherein m4 is equal to 0.41 when
M
tip
,
c
(
RL
)
is greater than or equal to 1.1 and is equal to 0.55 when
M
tip
,
c
(
RL
)
is less than 1.1.

118 more elements

A turbomachine for an aircraft comprising:

an annular casing;
and
a fan disposed inside the annular casing and mounted for rotation about an axial centerline, the fan including fan blades that extend radially outwardly toward the annular casing, a fan blade including:
an airfoil extending outwardly from a sloped root and including opposite pressure and suction sides extending longitudinally in span from the sloped root to an opposite tip, and extending axially in chord between opposite leading and trailing edges,
the airfoil further including stagger increasing between the sloped root and tip, camber decreasing therebetween, and chord length increasing outboard from the sloped root to barrel the airfoil along both the leading and trailing edges,
the airfoil further including maximum forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between a maximum barrel in the airfoil and the sloped root;
wherein the fan includes an average fan chord width of the fan blades (“c”), a diameter of the fan (“D”), a fan pressure ratio (“FPR”), and a redline corrected fan tip Mach number
(
“
M
tip
,
c
(
RL
)
”
)
according to a First Performance Factor (“FPF”),
wherein
FPF
=
[
c
0.15
·
D
]
⁢
/
[
[
FPR
-
1
0.4
]
/
M
tip
,
c
(
RL
)
]
-
1.23
,
wherein
⁢
m
1
·
[
M
tip
,
c
(
RL
)
-
1.1
]
+
9.14
>
FPF
>
m
2
·
[
M
tip
,
c
(
RL
)
-
1.1
]
,
and
wherein m1 is equal to 9.43 when
M
tip
,
c
(
RL
)
is greater than or equal to 1.1 and is equal to 27.02 when
M
tip
,
c
(
RL
)
is less than 1.1, and
wherein m2 is equal to 0.87 when
M
tip
,
c
(
RL
)
is greater than or equal to 1.1 and is equal to 3.34 when
M
tip
,
c
(
RL
)
is less than 1.1;
wherein the fan includes a fan hub-to-tip ratio (“HTR”), a fan blade count (“BC”), the fan pressure ratio (“FPR”), and the redline corrected fan tip Mach number
(
“
M
tip
,
c
(
RL
)
”
)
according to a Second Performance Factor (“SPF”),
wherein
SPF
=
π
4
⁢
(
1
-
HTR
2
)
/
(
BC
20
)
/
(
FPR
-
1
0.4
)
/
M
tip
,
c
(
RL
)
-
0.97
,
wherein
⁢
m
3
·
[
M
tip
,
c
(
RL
)
-
1.1
]
+
2.52
>
SPF
>
m
4
·
[
M
tip
,
c
(
RL
)
-
1.1
]
wherein m3 is equal to 3.17, and
wherein m4 is equal to 0.41 when
M
tip
,
c
(
RL
)
is greater than or equal to 1.1 and is equal to 0.55 when
M
tip
,
c
(
RL
)
is less than 1.1.

218 more elements

Dependencies are inferred from the claim text.

Facts

Application: 18/676,705Filed 29 May 2024
Priority: 14 Nov 2022
Published: 5 Feb 2026
Term ends: Not estimatedThe source records don’t support an estimate.

Classification6 codes

F04D 29/384
Blades: characterised by form
F04D 19/002
Axial-flow pumps: axial flow fans
F04D 29/324
For axial flow compressors: blades
Y02T 50/60
Aeronautics or air transport: efficient propulsion technologies, e.g. for aircraft

Family

Application17/986,544Continuation in part · filed 14 Nov 2022
Application18/138,442Continuation · filed 24 Apr 2023
Application18/511,128Continuation in part · filed 16 Nov 2023
Application18/654,444Continuation in part · filed 3 May 2024
Application18/676,705Continuation in part
Application18/511,128Continuation
Application18/138,442Continuation in part
US 11,661,851 B1Related patent
US 11,852,161 B1Related patent
US 12,669,131 B2Related patent
US 2024/0288000 A1Published application
US 2024/0288001 A1Published application
US 2026/0036136 A1This patent

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

Timeline

Citations

Open elsewhere

patentgrep

Loading patent…

Abstract

Facts

Application

18/676,705Filed 29 May 2024

Priority

14 Nov 2022

Published

5 Feb 2026

Term ends

Not estimatedThe source records don’t support an estimate.

Classification6 codes

F04D 29/384
Blades: characterised by form
F04D 19/002
Axial-flow pumps: axial flow fans
F04D 29/324
For axial flow compressors: blades
Y02T 50/60
Aeronautics or air transport: efficient propulsion technologies, e.g. for aircraft

Family

Application17/986,544Continuation in part · filed 14 Nov 2022

Application18/138,442Continuation · filed 24 Apr 2023

Application18/511,128Continuation in part · filed 16 Nov 2023

Application18/654,444Continuation in part · filed 3 May 2024

Application18/676,705Continuation in part

Application18/511,128Continuation

Application18/138,442Continuation in part

US 11,661,851 B1Related patent

US 11,852,161 B1Related patent

US 12,669,131 B2Related patent

US 2024/0288000 A1Published application

US 2024/0288001 A1Published application

US 2026/0036136 A1This patent

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