Geared turbofan engine having a reduced number of fan blades and improved acoustics

Patent metadata

Field	Value
Publication number	US-10184340-B2
Application number	US-201414769408-A
Country	US
Kind code	B2
Filing date	Feb 21, 2014
Priority date	Mar 15, 2013
Publication date	Jan 22, 2019
Grant date	Jan 22, 2019

Abstract

A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

First claim

The invention claimed is:

1. A turbofan engine, comprising:
a fan blade comprising:
an airfoil extending radially from a root section to a tip section, the airfoil having a leading edge and a trailing edge defining a curvature at a relative span height between the root section and the tip section;
wherein, in operation of the fan blade, the curvature determines a relative exit angle at the trailing edge, based on an incident flow velocity at the leading edge and a rotational velocity of the airfoil at the relative span height;
wherein the relative air angle is defined according to angle β2 or angle β2′ as provided in Table 1 herein for relative span heights between 75% and 95%, within a tolerance of two degrees (±2°); and
wherein the engine has less than twenty fan blades.

2. The turbofan engine of claim 1 , wherein the relative exit angle is defined according to angle β2 or angle β2′ as set forth in Table 1 herein for relative span heights from 75% to 95%, within a tolerance of two degrees (±2°).

3. The turbofan engine of claim 1 , wherein the relative exit angle is defined according to angle β2 or angle β2′ as provided in Table 1 herein, for relative span heights from 5% to 95% and within a tolerance of one degree (±1°).

4. The turbofan engine of claim 1 , wherein the exit pressure has an absolute value of at least 1.4 for each of the relative span heights from 75% to 95%.

5. The turbofan engine of claim 4 , wherein the exit pressure ratio has an absolute value of at least 1.4 for relative span heights between 95% and 98%.

6. The turbofan engine of claim 1 , wherein the relative air angle is defined according to angle β2 or angle β2′ as provided in Table 1 herein for relative span heights between 25% and 95%, within a tolerance of one degree (±1°).

7. The turbofan engine of claim 1 , wherein in operation of the fan blade the relative air angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is substantially constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

8. The turbofan engine of claim 7 , wherein the tolerance is 2% of the maximum value of the exit pressure ratio profile.

9. The turbofan engine of claim 7 , wherein the exit pressure ratio profile is non-decreasing for relative span heights from 50% to 95%.

10. The turbofan engine of claim 1 , wherein in operation of the turbofan engine the relative air angle determines an exit pressure ratio that has an absolute value of at least 1.3 for each of the relative span heights from 75% to 95%.

11. The turbofan engine of claim 10 , wherein the exit pressure ratio has an absolute value of at least 1.4 at a relative span height of 97%.

12. A turbofan engine, comprising:
a fan blade comprising:
an airfoil extending radially from a root section to a tip section, the airfoil having a leading edge and a trailing edge defining a curvature at a relative span height between the root section and the tip section;
wherein, in operation of the fan blade, the curvature determines a relative exit angle at the trailing edge, based on an incident flow velocity at the leading edge and a rotational velocity of the airfoil at the relative span height;
wherein the relative air angle is defined according to angle β2 or angle β2′ as provided in Table 1 herein for relative span heights between 75% and 95%, within a tolerance of two degrees (±2°); and
wherein the fan blade leading edge is thickened in the Z direction.

13. A turbofan engine, comprising:
a fan blade comprising:
an airfoil extending radially from a root section to a tip section, the airfoil having a leading edge and a trailing edge defining a curvature at a relative span height between the root section and the tip section;
wherein, in operation of the fan blade, the curvature determines a relative exit angle at the trailing edge, based on an incident flow velocity at the leading edge and a rotational velocity of the airfoil at the relative span height;
wherein the relative air angle is defined according to angle β2 or angle β2′ as provided in Table 1 herein for relative span heights between 75% and 95%, within a tolerance of two degrees (±2°); and
segmented acoustic liners, wherein at least one of the liner thickness, depth and porosity is variable across the liner.

Assignees

• United Technologies Corp

Inventors

• Baltas Constantine
• Gilson Jonathan

Classifications

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title