Turbomachinery inlet screen

Patent metadata

Field	Value
Publication number	US-10364746-B2
Application number	US-201415034176-A
Country	US
Kind code	B2
Filing date	Nov 3, 2014
Priority date	Nov 4, 2013
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

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, the first screen comprising an arched cross-sectional shape; and
a second screen including a third edge and a fourth edge, the second screen is planar and comprises a substantially flat cross-sectional shape;
wherein the first edge is secured to the third edge by a first flange and the second edge is secured to the fourth edge by a second flange,
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; and
wherein:
a cavity formed between the first screen and the second screen forms an annular ring with a hemisphere-shaped cross-section, an inner cylindrical surface, and an outer arcuate surface, and
the first screen forms the outer arcuate surface of the annular ring and the second screen forms the inner cylindrical surface of the annular ring.

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 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.

4. The turbomachinery inlet screen of claim 1 , 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.

5. The turbomachinery inlet screen of claim 4 , wherein the first angle is substantially the same as the second angle.

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

7. The turbomachinery inlet screen of claim 1 , wherein the first and second flange comprise corrosion-resistant steel.

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

9. 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, the first screen comprising an arched cross-sectional shape; and
a second screen including a third edge and a fourth edge, the second screen is planar and comprises a substantially flat cross-sectional shape;
wherein the first edge is secured to the third edge by a first flange and the second edge is secured to the fourth edge by a second flange,
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; and
wherein:
a cavity formed between the first screen and the second screen forms an annular ring with a hemisphere-shaped cross-section, an inner cylindrical surface, and an outer arcuate surface, and
the first screen forms the outer arcuate surface of the annular ring and the second screen forms the inner cylindrical surface of the annular ring.

10. The turbomachine of claim 9 , 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.

11. The turbomachine of claim 9 , 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.

12. The turbomachine of claim 9 , 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.

13. The turbomachine of claim 12 , wherein the first angle is substantially the same as the second angle.

14. The turbomachine of claim 9 , wherein:
the first screen and the second screen each comprise a plurality of wires; and
each plurality of wires comprises an austenitic nickel-chromium-based alloy.

15. The turbomachine of claim 9 , 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.

16. The turbomachine of claim 9 , wherein the inlet screen covers a 360 degree arc.

Assignees

• United Technologies Corp

Inventors

• Srinivasan Navindaran
• Adams Francis

Classifications

• F02C7/055 Primary

  with intake grids, screens or guards · 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

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• F04D29/701

  especially adapted for elastic fluid pumps · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic