Compressor inlet guide vanes

Patent metadata

Field	Value
Publication number	US-2017152860-A1
Application number	US-201514954146-A
Country	US
Kind code	A1
Filing date	Nov 30, 2015
Priority date	Nov 30, 2015
Publication date	Jun 1, 2017
Grant date	—

Abstract

A number of variations may include a method of optimizing inlet guide vane performance comprising: modifying an inlet guide vane to include at least one of a twist, a curve, a surface texture, a sealing feature, a tip leakage reduction feature, an airfoil having at least one component, or at least one channel.

First claim

What is claimed is:

1 . A method of optimizing inlet guide vane performance comprising: modifying an inlet guide vane to include at least one of a twist, a curve, a surface texture, a sealing feature, a tip leakage reduction feature, an airfoil having at least one component, or at least one channel.

2 . The method of claim 1 wherein the twist or the curve of the inlet guide vane tailors a pre-swirl level over a flow channel radius.

3 . The method of claim 1 wherein the surface texture of the inlet guide vane reduces pressure losses.

4 . The method of claim 1 wherein the sealing feature or the blocking feature on the inlet guide vane reduces secondary flow.

5 . The method of claim 1 wherein the airfoil or the at least one channel improves flow through a flow channel.

6 . A product comprising: an inlet guide vane having at least one of a twisted blade, a curved blade, a surface texture, a sealing feature, a blocking feature, an airfoil having at least one component, or at least one channel.

7 . The product of claim 6 wherein the twisted blade is twisted around at least one of an axis of rotation of the inlet guide vane or the leading edge of the inlet guide vane.

8 . The product of claim 6 wherein the curved blade is at least one of curved around a center line of the inlet guide vane or skewed around at least one of a leading edge or a trailing edge of the inlet guide vane.

9 . The product of claim 6 wherein the surface texture comprises an owl construction including a plurality of indentations which extend horizontally along a portion of a first and a second side of the blade from at least one of a trailing edge or a leading edge of the blade and increases in length as the blade width increases and wherein the plurality of indentations each taper.

10 . The product of claim 6 wherein the surface texture comprises a whale construction, wherein a first and a second side of the blade include a plurality of grooves which extend across the width of the blade.

11 . The product of claim 6 wherein the surface texture includes a golf ball pattern along at least one of a front surface, a rear surface, or a leading edge of the blade.

12 . The product of claim 6 wherein the seal feature comprises a winglet which includes a first and a second lip which extend from a top portion of the inlet guide vane and a first rib and a second rib which taper downward from the first and the second lip.

13 . The product of claim 6 wherein the tip leakage reduction feature comprises a spherical ball at a tip of the blade.

14 . The product of claim 6 wherein the airfoil comprises at least one flap mechanically attached to the inlet guide vane at an edge of the inlet guide vane, and wherein the at least one flap is constructed and arranged for at least one of rotational or translational movement.

15 . The product of claim 6 wherein the at least one channel comprises a plurality of channels which extend through the inlet guide vane.

16 . The product of claim 15 wherein the plurality of channels are each cylindrical.

17 . The product of claim 6 wherein the at least one channel comprises a single channel which extends through the inlet guide vane.

18 . The product of claim 17 wherein the single channel is rectangular.

19 . The product of claim 6 further comprising an inlet swirl device having an inlet port, a flow channel, and an outlet port, and wherein a plurality of inlet guide vanes are operatively attached to the flow channel.

20 . The product of claim 19 wherein a rotational axis of each inlet guide vane is placed at a quarter profile length from a leading edge of the inlet guide vane.

Assignees

• Borgwarner Inc

Inventors

• Miclea-Bleiziffer Mihai
• Karstadt Sascha
• Hanig Urs

Classifications

• F05D2250/12

  rectangular · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F04D29/4213

  suction ports · CPC title

• F05D2260/14

  Preswirling · CPC title

• F02B2037/125

  Control for avoiding pump stall or surge · CPC title