Turbomachinery inlet screen

Patent metadata

Field	Value
Publication number	US-2016281601-A1
Application number	US-201415034176-A
Country	US
Kind code	A1
Filing date	Nov 3, 2014
Priority date	Nov 4, 2013
Publication date	Sep 29, 2016
Grant date	—

Abstract

The present disclosure relates generally to an inlet screen for turbomachinery. The inlet screen may include a first screen and a second screen, wherein at least a portion of the first screen is offset from the second screen.

First claim

What is claimed:

1 . A turbomachinery inlet screen, comprising:
a first screen including a first edge and a second edge; and a second screen including a third edge and a fourth edge; wherein a first portion of the first screen is offset from the second screen; and wherein at least a second portion of the first screen is disposed adjacent the second screen.

2 . The turbomachinery inlet screen of claim 1 , wherein:
the first edge is disposed adjacent the third edge; the second edge is disposed adjacent the fourth edge; and the first portion is disposed between the first edge and the second edge.

3 . The turbomachinery inlet screen of claim 1 , wherein the first screen comprises an arched cross-sectional shape and the second screen comprises a substantially flat cross-sectional shape.

4 . The turbomachinery inlet screen of claim 1 , further comprising:
a first flange coupling the first edge to the third edge; and a second flange coupling the second edge to the fourth edge.

5 . The turbomachinery inlet screen of claim 4 , wherein at least one of the first and second screens comprises:
a plurality of first wires disposed substantially parallel to each of the first and second flanges; and a plurality of second wires disposed substantially perpendicular to each of the first and second flanges.

6 . The turbomachinery inlet screen of claim 4 , wherein at least one of the first and second screens comprises:
a plurality of first wires disposed at a first angle to each of the first and second flanges; and a plurality of second wires disposed at a second angle to each of the first and second flanges.

7 . The turbomachinery inlet screen of claim 6 , wherein the first angle is substantially the same as the second angle.

8 . The turbomachinery inlet screen of claim 1 , wherein:
the first screen and the second screen each comprise a plurality of wires; and the plurality of wires comprise an austenitic nickel-chromium-based alloy.

9 . The turbomachinery inlet screen of claim 4 , wherein the first and second flange comprise corrosion-resistant steel.

10 . The turbomachinery inlet screen of claim 1 , wherein the inlet screen covers a 360 degree arc.

11 . A turbomachine, comprising:
a compressor; a gas inlet arranged to direct a flow of gas to the compressor; and an inlet screen disposed between the gas inlet and the compressor, the inlet screen comprising:
a first screen including a first edge and a second edge; and
a second screen including a third edge and a fourth edge;
wherein a first portion of the first screen is offset from the second screen; and
wherein at least a second portion of the first screen is disposed adjacent the second screen.

12 . The turbomachine of claim 11 , wherein:
the first edge is disposed adjacent the third edge; the second edge is disposed adjacent the fourth edge; and the first portion is disposed between the first edge and the second edge.

13 . The turbomachine of claim 11 , wherein the first screen comprises an arched cross-sectional shape and the second screen comprises a substantially flat cross-sectional shape.

14 . The turbomachine of claim 11 , further comprising:
a first flange coupling the first edge to the third edge; and a second flange coupling the second edge to the fourth edge.

15 . The turbomachine of claim 14 , wherein at least one of the first and second screens comprises:
a plurality of first wires disposed substantially parallel to each of the first and second flanges; and a plurality of second wires disposed substantially perpendicular to each of the first and second flanges.

16 . The turbomachine of claim 14 , wherein at least one of the first and second screens comprises:
a plurality of first wires disposed at a first angle to each of the first and second flanges; and a plurality of second wires disposed at a second angle to each of the first and second flanges.

17 . The turbomachine of claim 16 , wherein the first angle is substantially the same as the second angle.

18 . The turbomachine of claim 11 , wherein:
the first screen and the second screen each comprise a plurality of wires; and the plurality of wires comprise an austenitic nickel-chromium-based alloy.

19 . The turbomachine of claim 11 , wherein the turbomachine is selected from the group consisting of: a gas turbine engine, an auxiliary power unit, a fan, a propeller, a windmill, a compressor and a turbine.

20 . The turbomachine of claim 11 , wherein the inlet screen covers a 360 degree arc.

Assignees

• United Technologies Corp

Inventors

• Sirinivasan Navindaran
• Adams Francis

Classifications

• F02C7/055 Primary

  with intake grids, screens or guards · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• F04D29/701

  especially adapted for elastic fluid pumps · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title