Inducer assembly for a turbine engine

Patent metadata

Field	Value
Publication number	US-12357933-B2
Application number	US-202418442719-A
Country	US
Kind code	B2
Filing date	Feb 15, 2024
Priority date	May 29, 2014
Publication date	Jul 15, 2025
Grant date	Jul 15, 2025

Abstract

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.

First claim

The invention claimed is:

1. A turbine engine comprising:
a compressor section which receives an ambient air stream and emits a compressed stream;
a combustion section which receives the compressed stream and emits a combustion stream which is at a higher temperature than the compressed stream;
a turbine section which receives the combustion stream and emits an exhaust stream which is at a lower temperature than the combustion stream;
a rotatable drive shaft coupling a portion of the turbine section with a portion of the compressor section and defining a rotational axis for the turbine engine;
a bypass conduit coupling the compressor section to the turbine section while bypassing at least the combustion section to supply either a portion of the ambient air stream or a portion of the compressed stream to the turbine section to define a bypass stream; and
at least one centrifugal separator fluidly coupled to the bypass stream, the at least one centrifugal separator having:
a body defining a centerline, wherein the body includes an outer annular wall defining a through passage;
a center body extend axially along the centerline within the through passage, spaced from the outer annular wall;
a separator inlet fluidly coupled to the through passage, receiving the bypass stream;
a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling;
an angular velocity increaser located within the through passage and coupled to the center body;
a flow splitter located downstream of the angular velocity increaser, the flow splitter having an inner annular wall spaced radially-inwardly from the outer annular wall, wherein the flow splitter is configured to split a radially-outward portion of the bypass stream from a radially-inward portion of the bypass stream such that the radially-outward portion of the bypass stream is a concentrated-particle stream and the radially-inward portion is the reduced-particle stream;
a first outlet passage defined by the inner annular wall that receives the reduced-particle stream, wherein the first outlet passage fluidly couples an inlet defined by an upstream edge of the inner annular wall and the separator outlet, and wherein a portion of the first outlet passage includes an axially-decreasing cross-section;
an angular velocity decreaser located downstream of the flow splitter; and
a second outlet passage defined by the outer annular wall and the inner annular wall, wherein the second outlet passage receives the concentrated-particle stream comprising separated particles, and wherein the second outlet passage includes an axially-increasing cross-section, such that a cross-section of the second outlet passage at the inlet is smaller than a cross-section of the second outlet passage downstream of the inlet.

2. The turbine engine of claim 1 , wherein the second outlet passage includes a particle outlet.

3. The turbine engine of claim 2 , wherein the particle outlet is located axially downstream of the angular velocity decreaser.

4. The turbine engine of claim 1 , wherein the angular velocity decreaser is located within the first outlet passage.

5. The turbine engine of claim 1 , wherein the angular velocity decreaser is coupled to the center body.

6. The turbine engine of claim 1 , wherein the center body has a first diameter measured at the angular velocity increaser and a second diameter measured at a portion of the center body located downstream of the angular velocity increaser and upstream of the angular velocity decreaser, wherein the first diameter is greater than the second diameter.

7. The turbine engine of claim 6 , wherein the second diameter of the center body is measured at the upstream edge or the inlet.

8. The turbine engine of claim 7 , wherein the center body further comprises a third diameter measured at the angular velocity decreaser, wherein the third diameter is greater than the second diameter.

9. The turbine engine of claim 8 , wherein the third diameter of the center body is less than the first diameter.

10. The turbine engine of claim 1 , wherein the second outlet passage further comprises vanes.

11. The turbine engine of claim 1 , wherein the axially-decreasing cross-section of the first outlet passage decreases from a first cross-section at the angular velocity decreaser to a second cross-section at the separator outlet, increasing the speed of the reduced-particle stream.

12. The turbine engine according to claim 1 , wherein the separator inlet and the separator outlet are co-axially aligned on the centerline.

13. The turbine engine according to claim 1 , wherein the second outlet passage includes a particle outlet that axially overlaps the portion of the first outlet passage with the axially-decreasing cross-section.

14. A turbine engine comprising:
a compressor section which receives an ambient air stream and emits a compressed stream;
a combustion section downstream of the compressor section;
a turbine section downstream of the combustion section;
a rotatable drive shaft coupling a portion of the turbine section with a portion of the compressor section and defining a rotational axis for the turbine engine;
a bypass conduit coupling the compressor section to the turbine section while bypassing at least the combustion section to supply either a portion of the ambient air stream or a portion of the compressed stream to the turbine section to define a bypass stream; and
at least one centrifugal separator fluidly coupled to the bypass stream, the at least one centrifugal separator having:
a body defining a centerline, wherein the body includes an outer annular wall defining a through passage;
a center body extending axially along the centerline within the through passage, spaced from the outer annular wall;
a separator inlet fluidly coupled to the through passage, receiving the bypass stream;
a fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling; and
an angular velocity increaser located within the through passage and coupled to the center body;
a flow splitter located downstream of the angular velocity increaser, the flow splitter having an inner annular wall spaced radially inwardly from the outer annular wall, wherein the flow splitter is configured to split a radially-outward portion of the bypass stream from a radially-inward portion of the bypass stream such that the radially-outward portion of the bypass stream is a concentrated-particle stream and the radially-inward portion is the reduced-particle stream;
a first outlet passage defined by the inner annular wall that receives the reduced-particle stream, wherein the first outlet passage fluidly couples an inlet defined by an upstream edge of the inner annular wall and a separator outlet,
an angular velocity decreaser coupled to the center body and located within the first outlet passage; and
a second outlet passage defined by the outer annular wall and the inner annular wall, wherein the second outlet passage receives the concentrated-particle stream comprising separated particles, wherein the second outlet passage includes a particle outlet located axially downstream of the angular velocity decreaser, and wherein the second outlet passage includes an axially-increasing cross-section, such that a cross-section of the second outlet passage at the inlet is smaller than a cross-section of the second outlet passage downstream of the inlet;
wherein the center body includes a first diameter measured at the angular velocity increaser and a second diameter m

Assignees

• Gen Electric

Inventors

• Stone Timothy Deryck
• Laskowski Gregory Michael
• Proctor Robert
• Stover Curtis
• Manning Robert Francis
• Correia Victor Hugo Silva
• Buhler Jared Peter
• Murray Robert Carl
• Bourassa Corey
• Pritchard Jr Byron Andrew
• Ratzlaff Jonathan Russell

Classifications

• Y02T50/60

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

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F02C7/052

  with dust-separation devices · CPC title