Characteristic distribution for rotor blade of booster rotor

Patent metadata

Field	Value
Publication number	US-11286779-B2
Application number	US-202016892145-A
Country	US
Kind code	B2
Filing date	Jun 3, 2020
Priority date	Jun 3, 2020
Publication date	Mar 29, 2022
Grant date	Mar 29, 2022

Abstract

A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a plurality of chord lines spaced apart in a spanwise direction. Each chord line of the plurality of chords lines is defined between the leading edge and the trailing edge and has a normalized chord value. From the hub, the normalized chord value decreases to a minimum value between about 20% to about 90% span and increases from the minimum value to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and fan.

First claim

What is claimed is:

1. A rotor for a turbofan booster section associated with a fan section of a gas turbine engine, the fan section including a fan driven by a shaft, the rotor downstream from the fan, and the rotor comprising:
a rotor blade having an airfoil extending from a root to a tip and having a leading edge and a trailing edge, the rotor blade having an inlet hub-to-tip radius ratio that is greater than 0.7 at the leading edge, the airfoil having a plurality of chord lines spaced apart in a spanwise direction from 0% span at the root to 100% span at the tip, each chord line of the plurality of chords lines defined between the leading edge and the trailing edge and having a normalized chord value, and from the hub, the normalized chord value decreases to a minimum value between 20% to 90% span and increases from the minimum value to the tip; and
a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and fan and to receive a portion of a fluid flow from the fan.

2. The rotor of claim 1 , wherein the normalized chord value has an absolute maximum value at the root.

3. The rotor of claim 1 , wherein between the minimum value and the tip, the normalized chord value has a second maximum value at the tip that is less than the absolute maximum value.

4. The rotor of claim 1 , wherein the normalized chord value decreases monotonically to the minimum value from the hub.

5. The rotor of claim 1 , wherein the minimum value is defined between 50% to 90% span.

6. The rotor of claim 1 , wherein the minimum value is defined between 60% to 80% span.

7. The rotor of claim 1 , wherein the minimum value is defined between 20% to 50% span.

8. The rotor of claim 1 , wherein the normalized chord value has an absolute maximum value at the tip.

9. The rotor of claim 1 , wherein the rotor disk is coupled to the fan to rotate with the fan, and the rotor disk is downstream from a fan core stator to receive the portion of the fluid flow from the fan.

10. A rotor for a turbofan booster section associated with a fan section of a gas turbine engine, the fan section including a fan driven by a shaft, the rotor downstream from the fan, and the rotor comprising:
a rotor blade having an airfoil extending from a root to a tip and having a leading edge and a trailing edge, the rotor blade having an inlet hub-to-tip radius ratio that is greater than 0.7 at the leading edge, the airfoil having a plurality of chord lines spaced apart in a spanwise direction from 0% span at the root to 100% span at the tip, each chord line of the plurality of chords lines defined between the leading edge and the trailing edge and having a normalized chord value, and from the hub, the normalized chord value decreases to a minimum value between 20% to 90% span and increases from the minimum value to a second maximum value at the tip, with the normalized chord value having an absolute maximum value at the root that is greater than the second maximum value; and
a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and fan and to receive a portion of a fluid flow from the fan.

11. The rotor of claim 10 , wherein the normalized chord value decreases monotonically to the minimum value from the hub.

12. The rotor of claim 10 , wherein the minimum value is defined between 50% to 90% span.

13. The rotor of claim 10 , wherein the minimum value is defined between 60% to 80% span.

14. The rotor of claim 10 , wherein the minimum value is defined between 20% to 50% span.

15. A rotor for a turbofan booster section associated with a fan section of a gas turbine engine, the fan section including a fan driven by a shaft, the rotor downstream from the fan, and the rotor comprising:
a rotor blade having an airfoil extending from a root to a tip and having a leading edge and a trailing edge, the rotor blade having an inlet hub-to-tip radius ratio that is greater than 0.7 at the leading edge, the airfoil having a plurality of chord lines spaced apart in a spanwise direction from 0% span at the root to 100% span at the tip, each chord line of the plurality of chord lines defined between the leading edge and the trailing edge and having a normalized chord value, and from the hub, the normalized chord value decreases monotonically to a minimum value between 20% to 90% span and increases from the minimum value to a second maximum value at the tip, with the normalized chord value having an absolute maximum value at the root that is greater than the second maximum value; and
a rotor disk coupled to the rotor blade configured to be coupled to the fan to rotate with the fan at the same speed as the fan and to receive a portion of a fluid flow from the fan.

16. The rotor of claim 15 , wherein the minimum value is defined between 50% to 90% span.

17. The rotor of claim 15 , wherein the minimum value is defined between 60% to 80% span.

Assignees

• Honeywell Int Inc

Inventors

• Nolcheff Nick
• Repp John
• Reynolds Bruce
• Gunaraj John

Classifications

• Y02T50/60

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

• F05D2240/24

  for turbines · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title