Asymmetric turbomachinery housing for thermal expansion

Patent metadata

Field	Value
Publication number	US-11401828-B2
Application number	US-201817044743-A
Country	US
Kind code	B2
Filing date	Dec 21, 2018
Priority date	Dec 21, 2018
Publication date	Aug 2, 2022
Grant date	Aug 2, 2022

Abstract

A turbomachinery according to an embodiment includes an impeller including at least one blade, and a casing for housing the impeller rotatably. A size of a gap between a tip of the blade and an inner surface of the casing during a stop of the impeller is formed non-uniformly over a circumferential direction of the impeller.

First claim

The invention claimed is:

1. A turbomachinery comprising:
an impeller including at least one blade; and
a casing for housing the impeller rotatably,
wherein a size of a gap between a tip of the blade and an inner surface of the casing during a non-operational state of the impeller during which the impeller is not rotating is formed non-uniformly over a circumferential direction of the impeller, and
wherein, during the non-operational state of the impeller, a center axis of the casing is not parallel to a rotational axis of the impeller.

2. The turbomachinery according to claim 1 , wherein a difference between a maximum value and a minimum value of the gap in a circumferential direction of the impeller during the non-operational state of the impeller is not less than 10% of an average value of the gap in the circumferential direction.

3. The turbomachinery according to claim 1 , wherein the casing has an inner circumferential edge formed into an elliptical shape.

4. The turbomachinery according to claim 1 ,
wherein the impeller is a radial flow impeller, and
wherein the casing is rotationally asymmetric about a center axis of the casing.

5. The turbomachinery according to claim 4 , wherein the casing includes:
a scroll part internally including a scroll flow passage where a fluid flows in the circumferential direction on a radially outer side of the impeller; and
a tongue part for separating the scroll flow passage from a flow passage on a radially outer side of the scroll flow passage, and

wherein, regarding the gap during the non-operational state of the impeller, the gap in the tongue part is larger than an average value of the gap in the circumferential direction.

6. The turbomachinery according to claim 5 ,
wherein, provided that an angular position of the tongue part is at 0 degrees in an angular range in the circumferential direction, and a direction, of an extending direction of the scroll flow passage, in which a flow-passage cross-sectional area of the scroll flow passage in a cross-section orthogonal to the extending direction gradually increases with distance from the tongue part along the extending direction, is a positive direction,
the gap during the non-operational state of the impeller has a maximum value during the non-operational state stop of the impeller within an angular range of not less than −90 degrees and not more than 0 degrees.

7. The turbomachinery according to claim 1 , wherein the size of the gap during the non-operational state of the impeller is formed non-uniformly over the circumferential direction of the impeller, in at least one of at least a part of a region between a leading edge of the blade and a position away by a distance of 20% of a total length of the tip from the leading edge toward a trailing edge of the blade, or at least a part of a region between the trailing edge and a position away by a distance of 20% of the total length from the trailing edge toward the leading edge.

8. The turbomachinery according to claim 1 ,
wherein the impeller is an axial flow impeller with a rotational axis thereof extending in a horizontal direction, and
wherein the casing is supported by a first support table and a second support table disposed away from the first support table in a direction along the rotational axis of the impeller.

9. The turbomachinery according to claim 8 ,
wherein the gap during the non-operational state of the impeller is larger than an average value of the gap in the circumferential direction, at an intermediate position between the first support table and the second support table and at a position, of a position along the circumferential direction, in a vertically upward direction of the impeller.

10. The turbomachinery according to claim 8 ,
wherein the gap during the non-operational state of the impeller is larger than an average value of the gap in the circumferential direction, at positions at both ends of the impeller along a direction of the rotational axis, and at a position, of a position along the circumferential direction, in a vertically downward direction of the impeller.

11. The turbomachinery according to claim 1 ,
wherein a variation in the size of the gap in the circumferential direction is larger during the non-operational state of the impeller than during a rotation of the impeller.

Assignees

• Mitsubishi Heavy Ind Engine & Turbocharger Ltd

Inventors

• Tomita Isao
• Takashima Reiko
• Fujita Yutaka

Classifications

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F04D29/622

  Adjusting the clearances between rotary and stationary parts · CPC title

• F04D29/284

  for compressors · CPC title

• F02B39/00

  Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00 · CPC title