Shroud for splitter and rotor airfoils of a fan for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11149552-B2
Application number	US-201916713469-A
Country	US
Kind code	B2
Filing date	Dec 13, 2019
Priority date	Dec 13, 2019
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.

First claim

What is claimed is:

1. A fan for a gas turbine engine, the fan comprising:
a rotor comprising at least one rotor stage including a rotatable disk defining a flowpath surface, an array of rotor airfoils extending outward from the flowpath surface, and each rotor air foil of the array of rotor airfoils having a rotor span dimension and being uninterrupted to provide a first airflow stream in a predetermined direction;
an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement, and each splitter airfoil of the array of splitter airfoils having a tip and a splitter span dimension and being uninterrupted to provide a second air flow stream in the predetermined direction that contributes to the first airflow stream, the splitter span dimension being less than the rotor span dimension; and
a shroud extending between the rotor airfoils and the splitter airfoils, the shroud being positioned relative to the tip to counter aerodynamic vortex leakage pressure loss at the tip into the second air flow stream.

2. The fan of claim 1 , wherein each rotor airfoil of the array of rotor airfoils and each splitter airfoil of the array of splitter airfoils being a single, continuous, and uninterrupted blade.

3. The fan of claim 2 , each rotor airfoil of the array of rotor airfoils and each splitter airfoil of the array of splitter airfoils being a single, continuous, and uninterrupted blade.

4. The fan of claim 1 , wherein the shroud is connected to the rotor airfoils at a position radially inward of a tip of each of the rotor airfoils and radially outward of a root of each of the rotor airfoils.

5. The fan of claim 4 , wherein the shroud is connected to the splitter airfoils at a position radially inward of the tip of each of the splitter airfoils and radially outward of a root of each of the splitter airfoils.

6. The fan of claim 4 , wherein the shroud is connected to a portion of the tip of each of the splitter airfoils.

7. The fan of claim 4 , wherein a first portion of the shroud is connected to a first splitter airfoil at a position radially inward of the tip of the first splitter airfoil and radially outward of a root of the first splitter airfoil, and wherein a second portion of the shroud is connected to a second splitter airfoil at the tip of the second splitter airfoil.

8. The fan of claim 7 , wherein a third portion of the shroud is disposed relative to a third splitter airfoil at a position adjacent to the tip of the third splitter airfoil.

9. The fan of claim 1 , wherein the shroud includes a plurality of linked shroud sections.

10. The fan of claim 1 , wherein a chord dimension of the splitter airfoil is less than a chord dimension of the rotor airfoil.

11. The fan of claim 1 , wherein the splitter airfoils and the rotor airfoils are disposed in a staggered and alternating arrangement.

12. The fan of claim 1 , wherein each splitter airfoil is located approximately midway between two adjacent rotor airfoils.

13. A gas turbine engine, comprising:
a turbomachinery core operable to produce a flow of combustion gases;
a turbine configured to extract energy from the combustion gases so as to drive a fan, wherein the fan includes:
a rotor comprising at least one rotor stage including a rotatable disk defining a flowpath surface, an array of rotor airfoils extending outward from the flowpath surface, and each rotor airfoil of the array of rotor airfoils having a rotor span dimension and being uninterrupted to provide a first airflow stream in a predetermined direction;
an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement, and each splitter airfoil of the array of splitter airfoils having a tip and a splitter span dimension and being uninterrupted to provide a second air flow stream in the predetermined direction that contributes to the first airflow stream, the splitter span dimension being less than the rotor span dimension; and
a shroud extending between the rotor airfoils and the splitter airfoils, the shroud being positioned relative to the tip to counter aerodynamic vortex leakage pressure loss at the tip into the second air flow stream.

14. The gas turbine engine of claim 13 , wherein the shroud is connected to the rotor airfoils at a position radially inward of a tip of each of the rotor airfoils and radially outward of a root of each of the rotor airfoils.

15. The gas turbine engine of claim 14 , wherein the shroud is connected to the splitter airfoils at a position radially inward of the tip of each of the splitter airfoils and radially outward of a root of each of the splitter airfoils.

16. The gas turbine engine of claim 14 , wherein the shroud is connected to a portion of the tip of each of the splitter airfoils.

17. The gas turbine engine of claim 14 , wherein a first portion of the shroud is connected to a first splitter airfoil at a position radially inward of the tip of the first splitter airfoil and radially outward of a root of the first splitter airfoil, and wherein a second portion of the shroud is connected to a second splitter airfoil at the tip of the second splitter airfoil.

18. The gas turbine engine of claim 17 , wherein a third portion of the shroud is disposed relative to a third splitter airfoil at a position adjacent to the tip of the third splitter airfoil.

19. The gas turbine engine of claim 13 , wherein the shroud includes a plurality of linked shroud sections.

20. The gas turbine engine of claim 13 , wherein a chord dimension of the splitter airfoil is less than a chord dimension of the rotor airfoil.

21. A fan for a gas turbine engine, the fan comprising:
a rotor comprising at least one rotor stage including a rotatable disk defining a flowpath surface, an array of rotor airfoils extending outward from the flowpath surface;
an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils, the rotor airfoils being disposed in a sequential arrangement; and
a shroud extending between the rotor airfoils and the splitter airfoils;
wherein the shroud is connected to the rotor airfoils at a position radially inward of a tip of each of the rotor airfoils and radially outward of a root of each of the rotor airfoils; and
wherein a first portion of the shroud is connected to a first splitter airfoil at a position radially inward of the tip of the first splitter airfoil and radially outward of a root of the first splitter airfoil, and wherein a second portion of the shroud is connected to a second splitter airfoil at the tip of the second splitter airfoil.

Assignees

• Gen Electric

Inventors

• Dipietro Jr Anthony Louis
• Alexander Tyler James
• Capozzi Joseph
• Wadia Aspi Rustom
• Breeze-Stringfellow Andrew

Classifications

• F04D29/324 Primary

  Blades · CPC title

• F01D5/142

  of the blades of successive rotor or stator blade-rows · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F04D29/544

  Blade shapes · CPC title

• F02K3/06

  with front fan · CPC title