TURBOMACHINE AND METHOD OF ASSEMBLY

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;

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.

2 . 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.

3 . The turbomachine of claim 1 , wherein FPF is within a range equal to or greater than 0 and equal to or less than 6.

4 . The turbomachine of claim 1 , wherein FPF is within a range equal to or greater than 1 and equal to or less than 2.

5 . The turbomachine of claim 1 , wherein M tip,c (RL) is within a range equal to or greater than 0.8 and equal to or less than 1.5.

6 . The turbomachine of claim 1 , wherein M tip,c (RL) is within a range equal to or greater than 0.9 and equal to or less than 1.4.

7 . The turbomachine of claim 1 , wherein ratio c/D is within a range equal to or greater than 0.1 and equal to or less than 0.3.

8 . The turbomachine of claim 1 , wherein FPR is within a range equal to or greater than 1.2 and equal to or less than 1.6.

9 . The turbomachine of claim 1 , wherein FPR is within a range equal to or greater than 1.3 and equal to or less than 1.5.

10 . The turbomachine of claim 1 , wherein FPR is within a range equal to or greater than 1.35 and equal to or less than 1.45.

11 . 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.

12 . The turbomachine of claim 1 , wherein the fan blade includes an airfoil portion made from a polymer matrix composite (PMC) material, a metallic leading edge, the ratio c/D is between 0.16 and 0.21, and the fan has between 16 and 25 fan blades.

13 . A turbomachine 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;

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 (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.

14 . The turbomachine of claim 13 , wherein SPF is within a range equal to or greater than 0.087 and equal to or less than 2.4.

15 . The turbomachine of claim 13 , wherein SPF is within a range equal to or greater than 1 and equal to or less than 2.

16 . The turbomachine of claim 13 , wherein M tip,c (RL) is within a range equal to or greater than 0.8 and equal to or less than 1.5.

17 . The turbomachine of claim 13 , wherein M tip,c (RL) is within a range equal to or greater than 0.9 and equal to or less than 1.4.

18 . The turbomachine of claim 13 , wherein HTR is within a range equal to or greater than 0.2 and equal to or less than 0.4.

19 . The turbomachine of claim 13 , wherein HTR is within a range equal to or greater than 0.25 and equal to or less than 0.35.

20 . The turbomachine of claim 13 , wherein FPR is within a range equal to or greater than 1.2 and equal to or less than 1.6.

21 . The turbomachine of claim 13 , wherein FPR is within a range equal to or greater than 1.3 and equal to or less than 1.5.

22 . The turbomachine of claim 13 , wherein FPR is within a range equal to or greater than 1.35 and equal to or less than 1.45.

23 . The turbomachine of claim 13 , wherein BC is within a range equal to or greater than 3 and equal to or less than 18.

24 . The turbomachine of claim 13 , wherein BC is within a range equal to or greater than 10 and equal to or less than 16.

25 . The turbomachine of claim 13 , 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.

26 . The turbomachine of claim 13 , wherein the fan blade includes an airfoil portion made from a polymer matrix composite (PMC) material, a metallic leading edge, the ratio c/D is between 0.16 and 0.21, and the fan has between 16 and 25 fan blades.

27 . 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;

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.

28 . The turbomachine of claim 27 , wherein FPF is within a range equal to or greater than −0.8 and equal to or less than 8.4.

29 . The turbomachine of claim 27 , wherein FPF is within a range equal to or greater than 0 and equal to or less than 6.

30 . The turbomachine of claim 27 , wherein FPF is within a range equal to or greater than 1 and equal to or less than 2.

31 . The turbomachine of claim 27 , wherein SPF is within a range equal to or greater than 0.087 and equal to or less than 2.4.

32 . The turbomachine of claim 27 , wherein SPF is within a range equal to or greater than 1 and equal to or less than 2.

33 . The turbomachine of claim 27 , wherein M tip,c (RL) is within a range equal to or greater than 0.8 and equal to or less than 1.5.

34 . The turbomachine of claim 27 , wherein M tip,c (RL) is within a range equal to or greater than 0.9 and equal to or less than 1.4.

35 . The turbomachine of claim 27 , wherein ratio c/D is within a range equal to or greater than 0.1 and equal to or less than 0.3.

36 . The turbomachine of claim 27 , wherein HTR is within a range equal to or greater than 0.2 and equal to or less than 0.4.

37 . The turbomachine of claim 27 , wherein HTR is within a range equal to or greater than 0.25 and equal to or less than 0.35.

38 . The turbomachine of claim 27 , wherein FPR is within a range equal to or greater than 1.2 and equal to or less than 1.6.

39 . The turbomachine of claim 27 , wherein FPR is within a range equal to or greater than 1.3 and equal to or less than 1.5.

40 . The turbomachine of claim 27 , wherein FPR is within a range equal to or greater than 1.35 and equal to or less than 1.45.

41 . The turbomachine of claim 27 , wherein BC is within a range equal to or greater than 3 and equal to or less than 18.

42 . The turbomachine of claim 27 , wherein BC is within a range equal to or greater than 10 and equal to or less than 16.

43 . The turbomachine of claim 27 , 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.

44 . The turbomachine of claim 27 , wherein the fan blade includes an airfoil portion made from a polymer matrix composite (PMC) material, a metallic leading edge, the ratio c/D is between 0.16 and 0.21, and the fan has between 16 and 25 fan blades.