US 2013/0199207 A1 · GAS TURBINE SYSTEM

Abstract

A gas turbine system including a compressor section, a combustor section and a turbine section, wherein the compressor section includes a first wheel and a second wheel having a center bore extending axially therethrough, and wherein the first wheel and the second wheel are relatively adjacent each other. Also included is a gap disposed between the first wheel and the second wheel, wherein airflow is directed radially inward within the gap toward the center bore of the second wheel with or without the help of impellers extending radially. The compressor section further includes an airflow manipulation device disposed within the gap, comprising of at least one or multiple vanes which may start in radial direction but extend at least partially into the center bore.

Claims19

Dependent claims

A gas turbine system having a compressor section, a combustor section and a turbine section, comprising:

a first wheel;
a second wheel having a center bore extending axially therethrough, wherein the first wheel and the second wheel are relatively adjacent each other;
a gap disposed between the first wheel and the second wheel, wherein airflow is directed radially inward within the gap toward the center bore of the second wheel;
and
an airflow manipulation device disposed within the gap and at least partially extending into the center bore, wherein the airflow manipulation device includes at least one vane extending axially into the center bore.

2 more elements

Dependencies are inferred from the claim text.

Gas turbine system

Life of this patent

Gas turbine system

Life of this patent

Abstract

Claims19