Integrally bladed rotor having double fillet

Patent metadata

Field	Value
Publication number	US-10502230-B2
Application number	US-201715652385-A
Country	US
Kind code	B2
Filing date	Jul 18, 2017
Priority date	Jul 18, 2017
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

An integrally bladed rotor according to an example of the present disclosure includes a hub, and a plurality of rotor airfoils integrally formed with the hub, and extending radially outward from an outer platform of the hub. Each rotor airfoil has a main body that extends radially outward from a root to a tip. A first fillet has a first radius that provides a transition from the outer platform of the hub, and a second fillet situated adjacent to and radially outward of the first fillet, that provides a transition between the first fillet and the main body. The second fillet has a second radius that is less than the first radius.

First claim

What is claimed is:

1. An integrally bladed rotor comprising:
a hub; and
a plurality of rotor airfoils integrally formed with the hub, and extending radially outward from an outer platform of the hub, each rotor airfoil comprising:
a main body extending radially outward from a root to a tip;
a first fillet having a first radius and providing a transition from the outer platform of the hub; and
a second fillet situated adjacent to and radially outward of the first fillet, and providing a transition between the first fillet and the main body, the second fillet having a second radius that is less than the first radius;
wherein the first and second fillets meet at a rim, and wherein for at least one of the rotor airfoils, a height of the rim, defined as a radial distance from a beginning point of the first fillet, is 1%-20% of a maximum radial length of the airfoil between the beginning point and the tip.

2. The integrally bladed rotor of claim 1 , wherein for each of the airfoils, a ratio of the first radius to the second radius is from 1.2:1 to 4:1.

3. The integrally bladed rotor of claim 2 , wherein for each of the airfoils, a ratio of the first radius to the second radius is from 2:1 to 3:1.

4. The integrally bladed rotor of claim 1 , wherein for at least one of the rotor airfoils, the first and second fillets extend around a leading edge of the rotor airfoil, a trailing edge of the rotor airfoil, or both.

5. The integrally bladed rotor of claim 1 , wherein for at least one of the rotor airfoils, the first and second fillets extend around a majority of a perimeter of the root.

6. The integrally bladed rotor of claim 1 , wherein the integrally bladed rotor is part of a compressor stage of a gas turbine engine.

7. The integrally bladed rotor of claim 1 , wherein the integrally bladed rotor is part of a fan section of a gas turbine engine.

8. An integrally bladed rotor comprising:
a hub; and
a plurality of rotor airfoils integrally formed with the hub, and extending radially outward from an outer platform of the hub, each rotor airfoil comprising:
a main body extending radially outward from a root to a tip;
a first fillet having a first radius and providing a transition from the outer platform of the hub; and
a second fillet situated adjacent to and radially outward of the first fillet, and providing a transition between the first fillet and the main body, the second fillet having a second radius that is less than the first radius;
wherein the first and second fillets meet at a rim, and wherein for at least one of the rotor airfoils, a ratio of a maximum width of the rim measured in a dimension perpendicular to a mean camber line of the rotor airfoil to a width of the main body measured along the same dimension between respective points where the second fillet ends on opposing outer sides of the airfoil is greater than 1:1 and less than or equal to 3:1.

9. An integrally bladed rotor comprising:
a hub; and
a plurality of rotor airfoils integrally formed with the hub, and extending radially outward from an outer platform of the hub, each rotor airfoil comprising:
a main body extending radially outward from a root to a tip;
a first fillet having a first radius and providing a transition from the outer platform of the hub; and
a second fillet situated adjacent to and radially outward of the first fillet, and providing a transition between the first fillet and the main body;
wherein the first and second fillets meet at a rim that provides a stepped platform between the first and second fillets, and a ratio of the first radius to the second radius is from 0.5:1 to 1.2:1.

10. A gas turbine engine comprising:
a compressor comprising a plurality of stages;
a fan operable to deliver air to the compressor; and
a combustor operable to ignite a mixture of fuel and compressed air from the compressor;
wherein at least one of the stages comprises an integrally bladed rotor having a hub and a plurality of rotor airfoils extending radially outward from the hub, each of the rotor airfoils including:
a main body extending radially outward from a root to a tip;
a first fillet having a first radius and providing a transition from the outer platform of the hub; and
a second fillet situated adjacent to and radially outward of the first fillet, and providing a transition between the first fillet and the main body, the second fillet having a second radius that is less than the first radius;
wherein the first and second fillets meet at a rim, and wherein the rim of at least one rotor airfoil of one of the stages has a different height defined as a radial distance from a beginning point of the first fillet, different maximum width measured along a dimension perpendicular to an airfoil mean camber line, or both than the rim of at least one rotor airfoil of another of the stages.

11. The gas turbine engine of claim 10 , wherein each of the plurality of the stages comprises an integrally bladed rotor comprising rotor airfoils having the first fillet and second fillet.

12. The gas turbine engine of claim 10 , wherein the compressor comprises a high pressure compressor and a low pressure compressor, and said at least one of the stages is a first stage of the high pressure compressor.

13. The gas turbine engine of claim 10 , wherein for each of the airfoils having the first and second fillet, a ratio of the first radius to the second radius is from 1.2:1 to 4:1.

14. The gas turbine engine of claim 10 , wherein for each of the airfoils having the first and second fillet, a ratio of the first radius to the second radius is from 2:1 to 3:1.

15. The gas turbine engine of claim 10 , wherein for at least one of the rotor airfoils having the first and second fillet, the first and second fillets extend around a leading edge of the rotor airfoil, a trailing edge of the rotor airfoil, or both.

16. The gas turbine engine of claim 10 , wherein for at least one of the rotor airfoils having the first and second fillet, the first and second fillets extend around a majority of a perimeter of the root.

17. The gas turbine engine of claim 10 , wherein for at least one of the rotor airfoils, a height of the rim, defined as a radial distance from a beginning point to the first fillet, is 1%-20% of a maximum radial length of the airfoil between the beginning point and the tip.

18. The gas turbine engine of claim 10 , wherein for at least one of the rotor airfoils, a ratio of a maximum width of the rim measured in a dimension perpendicular to a mean camber line of the rotor airfoil to a width of the main body measured along the same dimension between respective points where the second fillet ends on opposing outer sides of the airfoil is greater than 1:1 and less than or equal to 3:1.

Assignees

• United Technologies Corp

Inventors

• Anderson Carney R

Classifications

• F05D2250/713

  inflexed · CPC title

• F05D2250/71

  curved · CPC title

• F04D29/384 Primary

  characterised by form · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title