Partially shrouded gas turbine engine fan

Patent metadata

Field	Value
Publication number	US-10619483-B2
Application number	US-201715819047-A
Country	US
Kind code	B2
Filing date	Nov 21, 2017
Priority date	Nov 21, 2017
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

Abstract

An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a turbine section;
a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan, wherein the fan comprises:
a hub;
a plurality of blade bodies extending radially outward from the hub to a first partial shroud;
a plurality of blade tips extending radially outward from the first partial shroud;
wherein the first partial shroud is positioned at a radial intersection with a boundary layer ingestion of a fan inlet in the range of 70% span to 90% span, where the hub defines 0% span and a radially outermost tip of the blade tips defines 100% span.

2. The gas turbine engine of claim 1 , further comprising an outer shroud radially outward of the plurality of blade tips, and wherein the blade tips span from the partial shroud to the outer shroud.

3. The gas turbine engine of claim 1 , wherein a quantity of blade tips in said plurality of blade tips is a multiple of a quantity of blade bodies in the plurality of blade bodies.

4. The gas turbine engine of claim 3 , wherein a subset of the plurality of blade tips is aligned with corresponding blade bodies.

5. The gas turbine engine of claim 1 , wherein a quantity of blade tips in said plurality of blade tips is not a whole number multiple of a quantity of blade bodies in the plurality of blade bodies.

6. The gas turbine engine of claim 1 , wherein the gas turbine engine is a boundary layer ingestion engine.

7. The gas turbine engine of claim 1 , further comprising a second partial shroud radially inward of the first partial shroud.

8. The gas turbine engine of claim 1 , wherein the first partial shroud and the plurality of blade tips are a single integral component.

9. The gas turbine engine of claim 1 , wherein the first partial shroud is attached to each blade tip in the plurality of blade tips.

10. The gas turbine engine of claim 1 , wherein the first partial shroud extends at least a full axial length of the plurality of blade tips, relative to an axis defined by the fan.

11. The gas turbine engine of claim 1 , wherein the first partial shroud extends less than a full axial length of the plurality of blade tips, relative to an axis defined by the fan.

12. The gas turbine engine of claim 1 , wherein an axial length of each blade tip in the plurality of blade tips is less than an axial length of each blade body in the plurality of blade bodies.

13. The gas turbine engine of claim 12 , wherein a ratio of the axial length of each of the blade bodies in the plurality of blade bodies to the axial length of each of the blade tips in the plurality of blade tips is less than or equal to two.

14. A fan for a gas turbine engine comprising:
a hub;
a first partial shroud radially outward of the hub;
a plurality of blade bodies extending from the hub to the partial shroud;
a plurality of blade tips extending radially outward from the partial shroud;
wherein the first partial shroud is positioned at a radial intersection with a boundary layer ingestion of a fan inlet in the range of 70% span to 90% span, where the hub defines 0% span and a radially outermost tip of the blade tips defines 100% span.

15. The fan of claim 14 , wherein a quantity of blade tips in said plurality of blade tips is a multiple of a quantity of blade bodies in the plurality of blade bodies.

16. The fan of claim 15 , wherein a subset of the plurality of blade tips is aligned with corresponding blade bodies.

17. The fan of claim 14 , further comprising a second partial shroud disposed between said hub and said first partial shroud.

Assignees

• United Technologies Corp

Inventors

• Voytovych Dmytro Mykolayovych
• Staroselsky Alexander
• Sharma Om P
• Suciu Gabriel L
• Merry Brian
• Alvanos Ioannis

Classifications

• B64D27/20

  within, or attached to, fuselages · CPC title

• F05D2260/15

  Load balancing · CPC title

• F01D5/3061

  by welding, brazing · CPC title

• F04D29/326

  comprising a rotating shroud · CPC title

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title