Mistuned rotors and methods for manufacture

Patent metadata

Field	Value
Publication number	US-10876409-B2
Application number	US-201816183448-A
Country	US
Kind code	B2
Filing date	Nov 7, 2018
Priority date	Nov 7, 2018
Publication date	Dec 29, 2020
Grant date	Dec 29, 2020

Abstract

A rotor includes a plurality of airfoils and each airfoil has a span that extends from 0% at a root to 100% at a tip, a chord that extends from 0% at a leading edge to 100% at a trailing edge and a pressure side opposite a suction side. The pressure side of each airfoil has a pressure side surface shape and the suction side of each airfoil has a suction side surface shape based on an operating state of the rotor. Each airfoil has the same suction side surface shape between 10% and 90% of the chord and between 80% and 100% of the span at a first state. At least one first airfoil has a different suction side surface shape between 10% and 90% of the chord and between 80% and 100% of the span than at least one second airfoil at a static state of the rotor.

First claim

What is claimed is:

1. A rotor for a gas turbine engine, comprising:
a plurality of airfoils each extending from a root to a tip and having a leading edge opposite a trailing edge, each airfoil of the plurality of airfoils having a span that extends from 0% at the root to 100% at the tip, a chord that extends from 0% at the leading edge to 100% at the trailing edge and a pressure side opposite a suction side, the pressure side of each airfoil of the plurality of airfoils having a pressure side surface shape based on an operating state of the rotor and the suction side of each airfoil of the plurality of airfoils having a suction side surface shape based on the operating state of the rotor;
each airfoil of the plurality of airfoils has the same suction side surface shape between 10% and 90% of the chord and between 80% and 100% of the span at a first operating state of the rotor; and
at least one first airfoil of the plurality of airfoils has a different suction side surface shape between 10% and 90% of the chord and between 80% and 100% of the span than at least one second airfoil of the plurality of airfoils at a static state of the rotor.

2. The rotor of claim 1 , wherein in the first operating state of the rotor, the rotor has a rotational speed in which a tip speed of the rotor is greater than 900 feet per second.

3. The rotor of claim 1 , wherein each airfoil of the plurality of airfoils has the same pressure side surface shape between 10% and 90% of the chord and between 80% and 100% of the span in the first operating state of the rotor.

4. The rotor of claim 1 , wherein the at least one first airfoil of the plurality of airfoils is directly adjacent to the at least one second airfoil of the plurality of airfoils.

5. The rotor of claim 1 , wherein the pressure side surface shape between 0% and 50% of the span of the at least one first airfoil of the plurality of airfoils is different than the pressure side surface shape between 0% and 50% of the span of the at least one second airfoil of the plurality of airfoils at the first operating state of the rotor.

6. The rotor of claim 5 , wherein the at least one first airfoil of the plurality of airfoils has at least one local thickness between 0% and 50% of the span that is different than at least one second local thickness of the at least one second airfoil of the plurality of airfoils between 0% and 50% of the span.

7. The rotor of claim 1 , wherein the pressure side surface shape between 0% and 50% of the span of the at least one first airfoil of the plurality of airfoils is different than the pressure side surface between 0% and 50% of the span of the at least one second airfoil of the plurality of airfoils at the static state of the rotor.

8. A method for manufacturing a plurality of airfoils associated with a rotor for a gas turbine engine, the method comprising:
determining, by a processor, a first working shape for a suction side surface of each airfoil of the plurality of airfoils at a first operating state of the rotor, each airfoil of the plurality of airfoils including a suction side having the suction side surface opposite a pressure side having a pressure side surface, a leading edge opposite a trailing edge and extending from a root to a tip, each airfoil of the plurality of airfoils having a span that extends from 0% at the root to 100% at the tip and a chord that extends from 0% at the leading edge to 100% at the trailing edge, and the first working shape for the suction side surface is the same for each airfoil of the plurality of airfoils between 10% and 90% of the chord and 80% and 100% of the span;
determining, by the processor, a second working shape for at least one of the suction side surface and the pressure side surface of at least one first airfoil of the plurality of airfoils between 0% and 50% of the span that is different than a third working shape for at least one of the suction side surface and the pressure side surface of at least one second airfoil of the plurality of airfoils between 0% and 50% of the span at the first operating state of the rotor;
determining, by the processor, a static shape for each airfoil of the plurality of airfoils at a static state of the rotor, and the static shape is based on at least one of the first working shape, the second working shape and the third working shape; and
manufacturing each airfoil of the plurality of airfoils based on the static shape.

9. The method of claim 8 , further comprising:
performing a hot to cold geometry transformation, by the processor, to determine the static shape for the at least one first airfoil of the plurality of airfoils based on the first working shape and the second working shape.

10. The method of claim 8 , further comprising:
performing a hot to cold geometry transformation, by the processor, to determine the static shape for the at least one second airfoil of the plurality of airfoils based on the first working shape and the third working shape.

11. The method of claim 8 , further comprising:
determining, by the processor, the second working shape based on a change in a thickness of the at least one first airfoil of the plurality of airfoils between 0% span and 50% span to obtain a difference between a first natural vibratory frequency of the at least one first airfoil of the plurality of airfoils and a second natural vibratory frequency of the at least one second airfoil of the plurality of airfoils.

12. The method of claim 8 , further comprising:
determining, by the processor, the second working shape for the pressure side surface of the at least one first airfoil of the plurality of airfoils, with the suction side surface of the at least one first airfoil of the plurality of airfoils the same as the suction side surface of the at least one second airfoil of the plurality of airfoils.

13. A rotor for a gas turbine engine, comprising:
a plurality of airfoils each extending from a root to a tip and having a leading edge opposite a trailing edge, each airfoil of the plurality of airfoils having a span that extends from 0% at the root to 100% at the tip, and a pressure side opposite a suction side, the pressure side of each airfoil of the plurality of airfoils having a pressure side surface shape based on an operating state of the rotor and the suction side of each airfoil of the plurality of airfoils having a suction side surface shape based on the operating state of the rotor;
each airfoil of the plurality of airfoils has the same suction side surface shape and the same pressure side surface shape between 80% and 100% of the span at a first operating state of the rotor;
at least one first airfoil of the plurality of airfoils has the pressure side surface shape between 0% and 50% of the span that is different than the pressure side surface shape between 0% and 50% of the span of at least one second airfoil of the plurality of airfoils at the first operating state of the rotor; and
the at least one first airfoil of the plurality of airfoils has a different suction side surface shape between 80% and 100% of the span than the at least one second airfoil of the plurality of airfoils at a static state of the rotor.

14. The rotor of claim 13 , wherein in the first operating state of the rotor, the rotor has a rotational speed in which a tip speed of the rotor is greater than 900 feet per second.

15. The rotor of claim 13 , wherein the at least one first airfoil of the plurality of airfoils is directly adjacent to the at least one second airfoil of the plurality of airfoils.

16. The rotor of claim 13 , wherein the at least one first airfoil of t

Assignees

• Honeywell Int Inc

Inventors

• Nolcheff Nick
• Repp John
• Gunaraj John A
• Gebre-Giorgis Yoseph

Classifications

• B23P2700/01

  Aircraft parts · CPC title

• F04D29/324

  Blades · CPC title

• B23P15/04

  turbine or like blades from several pieces · CPC title

• F01D5/141

  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