US2026036136A1PendingUtilityA1
Turbomachine and method of assembly
Est. expiryNov 14, 2042(~16.3 yrs left)· nominal 20-yr term from priority
Inventors:YAO JIXIANWOOD TREVOR HRAMAKRISHNAN KISHORESOLOMON WILLIAM JJOTHIPRASAD GIRIDHARKING AARON J
F04D 19/002F04D 29/384F04D 29/324Y02T50/60
53
PatentIndex Score
0
Cited by
0
References
0
Claims
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.
Claims
exact text as granted — not AI-modifiedWhat is claimed is:
1 . 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 m 1 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 m 2 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.
2 . The turbomachine of claim 1 , wherein the forward sweep at the tip transitions to a maximum aft sweep inwardly along the leading edge in the barrel, and decreases in aft magnitude to non-forward sweep at the root.
3 . The turbomachine of claim 1 , wherein the airfoil further includes sharp leading and trailing edges from the root to tip and gradually increases to a maximum thickness along a midchord region therebetween.
4 . The turbomachine of claim 1 , wherein the airfoil further includes low sweep near the root being less than about half the maximum sweep in the airfoil thereabove.
5 . The turbomachine of claim 1 , wherein:
FPF is within a range equal to or greater than −0.8 and equal to or less than 8.4; M tip,c (RL) is within a range equal to or greater than 0.8 and equal to or less than 1.5; ratio c/D is within a range equal to or greater than 0.1 and equal to or less than 0.3; and FPR is within a range equal to or greater than 1.2 and equal to or less than 1.6.
6 . The turbomachine of claim 1 , wherein the turbomachine has a gear ratio within a range equal to or greater than 3.2 and equal to or less than 5.0.
7 . The turbomachine of claim 1 , wherein the ratio c/D is between 0.16 and 0.21, and the fan has between 16 and 25 fan blades.
8 . 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 m 3 is equal to 3.17, and
wherein m 4 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.
9 . The turbomachine of claim 8 , wherein the forward sweep at the tip transitions to a maximum aft sweep inwardly along the leading edge in the barrel, and decreases in aft magnitude to non-forward sweep at the root.
10 . The turbomachine of claim 8 , wherein the airfoil further includes sharp leading and trailing edges from the root to tip and gradually increases to a maximum thickness along a midchord region therebetween.
11 . The turbomachine of claim 8 , wherein the airfoil further includes low sweep near the root being less than about half the maximum sweep in the airfoil thereabove.
12 . The turbomachine of claim 8 , wherein:
SPF is within a range equal to or greater than 0.087 and equal to or less than 2.4;
M
tip
,
c
(
RL
)
is within a range equal to or greater than 0.8 and equal to or less than 1.5;
HTR is within a range equal to or greater than 0.2 and equal to or less than 0.4;
FPR is within a range equal to or greater than 1.2 and equal to or less than 1.6; and
BC is within a range equal to or greater than 3 and equal to or less than 18.
13 . The turbomachine of claim 8 , wherein the turbomachine has a gear ratio within a range equal to or greater than 3.2 and equal to or less than 5.0.
14 . 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 m 1 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 m 2 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 m 3 is equal to 3.17, and
wherein m 4 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.
15 . The turbomachine of claim 14 , wherein the forward sweep at the tip transitions to a maximum aft sweep inwardly along the leading edge in the barrel, and decreases in aft magnitude to non-forward sweep at the root.
16 . The turbomachine of claim 14 , wherein the airfoil further includes sharp leading and trailing edges from the root to tip and gradually increases to a maximum thickness along a midchord region therebetween.
17 . The turbomachine of claim 14 , wherein the airfoil further includes low sweep near the root being less than about half the maximum sweep in the airfoil thereabove.
18 . The turbomachine of claim 14 , wherein:
FPF is within a range equal to or greater than −0.8 and equal to or less than 8.4; SPF is within a range equal to or greater than 0.087 and equal to or less than 2.4;
M
tip
,
c
(
RL
)
is within a range equal to or greater than 0.8 and equal to or less than 1.5; and
FPR is within a range equal to or greater than 1.2 and equal to or less than 1.6.
19 . The turbomachine of claim 14 , wherein:
ratio c/D is within a range equal to or greater than 0.1 and equal to or less than 0.3; HTR is within a range equal to or greater than 0.2 and equal to or less than 0.4; and BC is within a range equal to or greater than 3 and equal to or less than 18.
20 . The turbomachine of claim 14 , wherein the turbomachine has a gear ratio within a range equal to or greater than 3.2 and equal to or less than 5.0.Join the waitlist — get patent alerts
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