Forward-swept impellers and gas turbine engines employing the same

Patent metadata

Field	Value
Publication number	US-9970452-B2
Application number	US-201514623761-A
Country	US
Kind code	B2
Filing date	Feb 17, 2015
Priority date	Feb 17, 2015
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a shaft having a rotational axis; and
a forward-swept impeller mounted to the shaft, the forward-swept impeller comprising:
an inboard impeller section;
an outboard impeller section circumscribing the inboard impeller section, the outboard impeller section joined to the inboard impeller section along an annular interface concentric with the rotational axis, the annular interface having a radius equal to a free ring radius of the forward-swept impeller; and
a plurality of hub flow paths defined by the outboard impeller section each of the plurality of hub flow paths having an axial length of AX FLOW , as taken along the rotational axis;

wherein each of the plurality of hub flow paths has a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit and that forms an acute angle θ with a radius of the forward-swept impeller;
wherein the forward-swept impeller has a first Center of Gravity (CG) considered as a whole, the outboard impeller section has a second CG, and the second CG is offset from the first CG in the forward direction by an axial offset AX OFF that is at least 10% AX FLOW .

2. The gas turbine engine of claim 1 wherein the acute angle θ has a value between 5 and 15 degrees.

3. The gas turbine engine of claim 1 further comprising a diffuser positioned radially outboard of the forward-swept impeller and receiving airflow discharged therefrom, the diffuser having a flow passage tilted in the forward direction by an angle equivalent to θ.

4. The gas turbine engine of claim 1 further comprising a shroud circumscribing the forward-swept impeller and having a downstream portion curling in the forward direction.

5. The gas turbine engine of claim 1 further comprising a diffuser positioned radially outboard of the forward-swept impeller and configured to receive compressed airflow discharged therefrom, the diffuser having a flow passage with a leading edge axially offset in the forward direction from a forward-most point of the plurality of hub flow paths.

6. The gas turbine engine of claim 1 wherein the forward-swept impeller further comprises:
a central disk having a backface; and
a plurality of blades extending from central disk;
wherein the inboard impeller section encompasses a volumetric majority of the central disk, while the outboard impeller section encompasses a majority of the backface of the central disk by surface area.

7. A forward-swept impeller, comprising:
an inboard impeller section;
an outboard impeller section circumscribing the inboard impeller section, the outboard impeller section joined to the inboard impeller section along an annular interface concentric with a rotational axis of the forward-swept impeller, the annular interface having a radius equal to a free ring radius of the forward-swept impeller; and
a plurality of hub flow paths defined by the outboard impeller section, each of the plurality of hub flow paths having an axial length of AX FLOW , as taken along the rotational axis;
wherein the forward-swept impeller has a first Center of Gravity (CG) considered as a whole, the outboard impeller section has a second CG, and the second CG is offset from the first CG in a forward direction by an axial offset AX OFF that is at least 10% AX FLOW ; and
wherein each of the plurality of hub flow paths has a flow path exit that is tilted in the forward direction, as taken along a line tangent to the flow path exit and forming an acute angle θ with a radius of the forward-swept impeller intersecting the first CG.

8. The forward-swept impeller of claim 7 wherein the acute angle θ has a value between 5 and 15 degrees.

9. The forward-swept impeller of claim 7 further comprising:
a central disk having a backface; and
a plurality of blades extending from central disk;
wherein the inboard impeller section encompasses a volumetric majority of the central disk, while the outboard impeller section encompasses a majority of the backface of the central disk by surface area.

10. The forward-swept impeller of claim 7 wherein, as considered in cross-section as taken along a plane containing the rotational axis, the plurality of hub flow paths is located entirely forward of a plane orthogonal to the rotational axis and containing the radius of the forward-swept impeller intersecting the first CG.

Assignees

• Honeywell Int Inc

Inventors

• Conner Richard David
• Barton Michael Todd
• Gebre-Giorgis Yoseph
• Kington Harry Lester
• Repp John

Classifications

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F05D2250/38

  angled, e.g. sweep angle · CPC title

• F04D29/284 Primary

  for compressors · CPC title

• F02C3/09

  of the centripetal type · CPC title