# US 9,435,206 B2 · Flow inducer for a gas turbine system

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- Number: US 9,435,206 B2
- Document ID: US9435206B2
- Status: Granted
- Kind: B2
- Application number: 13/610,839
- Filed: 2012-09-11
- Published: 2014-03-13
- Granted: 2016-09-06
- Earliest claimed: 2012-09-11
- Assignees: General Electric Company
- Applicants: Richard William Johnson; Bradley James Miller; David Martin Johnson
- Inventors: Richard William Johnson; Bradley James Miller; David Martin Johnson
- Web page: https://patentgrep.com/patent/US9435206B2

## CPC

- F01D 5/087: {in the radial passages of the rotor disc}
- F01D 5/081: {Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence)}
- F01D 5/084: {the fluid circulating at the periphery of a multistage rotor, e.g. of drum type}
- F01D 5/187: {Convection cooling}
- F01D 25/12: Cooling
- F05D 2220/32: in gas turbines
- F05D 2260/2212: by creating turbulence
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A system includes an inducer assembly configured to receive a fluid flow from compressor fluid source and to turn the fluid flow in a substantially circumferential direction into the exit cavity. The inducer assembly includes multiple flow passages. Each flow passage includes an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet. The first wall portion includes a first surface adjacent the outlet that extends into the exit cavity.

## Claims

### Claim 1

A system, comprising:
an inducer assembly configured to receive a fluid flow from a fluid source and to turn the fluid flow in a substantially circumferential direction into an exit cavity, and the inducer assembly comprises:
a plurality of flow passages, each flow passage comprises an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet, and the first wall portion comprises a first surface adjacent the outlet that extends into the exit cavity, wherein the first wall portion of each flow passage comprises a second surface, wherein the second surface is configured to turn the fluid flow in the substantially circumferential direction and to enable exit of the fluid flow from the outlet in a substantially tangential direction relative to an annular cross-sectional area of the exit cavity, and wherein the first wall portion comprises a groove, the first wall portion and the second surface are separate parts, and the second surface is disposed on an insert within the groove.

### Claim 2

A system, comprising:
an inducer assembly configured to receive a fluid flow from a fluid source and to turn the fluid flow in a substantially circumferential direction into an exit cavity, and the inducer assembly comprises:
a plurality of flow passages, each flow passage comprises an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet, and the first wall portion comprises a first surface adjacent the outlet that extends into the exit cavity; and
an annular support structure circumferentially configured to be disposed about a rotational axis of a gas turbine engine having an inner surface adjacent the exit cavity and an outer surface, and the plurality of flow passages are disposed circumferentially about the support structure between the inner surface and the outer surface, and wherein the inner surface of a portion of the annular support structure adjacent an aft portion of the first surface of each flow passage extends in a radial direction beyond the aft portion of the first surface and is configured to minimize flow tripping, the second wall portion comprises a second surface, and a forward portion of the second surface of each flow passage extends in the radial direction beyond an adjacent portion of the inner surface of the support structure and is configured to minimize flow tripping.