Reduced fan containment threat through liner and blade design

Patent metadata

Field	Value
Publication number	US-10731511-B2
Application number	US-201314432356-A
Country	US
Kind code	B2
Filing date	Feb 22, 2013
Priority date	Oct 1, 2012
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.

First claim

What is claimed is:

1. A blade containment system comprising:
a plurality of circumferentially-arranged rotatable blades, each blade having a blade compliance; and
an annular containment structure radially outward from the rotatable blades, the annular containment structure including a liner having a liner compliance, the blade compliance and the liner compliance being configured such that a strain induced on a respective one of the rotatable blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture, wherein the liner includes an inner liner and an outer liner, the inner liner being composed of an adbradable layer and a honeycomb, a hollow cavity located radially between the honeycomb and the outer liner, a purge channel connecting to the hollow cavity and a vent configured to selectively ventilate a gas from the hollow cavity, wherein the vent includes a plurality of vent openings and is located downstream of the rotatable blades, the purge channel extending adjacent another, downstream honeycomb, and at least a portion of the plurality of vent openings are radially inwards of the downstream honeycomb.

2. The system as recited in claim 1 , wherein each of the rotatable blades includes an interior cavity.

3. The system as recited in claim 2 , wherein the interior cavity is elongated along a chord-direction of each of the rotatable blades.

4. The system as recited in claim 2 , wherein the rotatable blades are made of aluminum alloy.

5. The system as recited in claim 1 , wherein the inner liner is a modular cartridge.

6. The system as recited in claim 1 , wherein the downstream honeycomb includes intercellular slots that connect adjacent cells of the downstream honeycomb to the plurality of vent openings.

7. The system as recited in claim 6 , wherein a portion of the plurality of vent openings open radially outwards.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Robertson Jr Thomas J
• Voleti Sreenivasa R
• Costa Mark W
• Clarkson Steven

Classifications

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2240/24

  for turbines · CPC title

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• F05D2220/30

  in turbines · CPC title

• F05D2300/612

  Foam · CPC title