Patent ID: 9291063
Filing Date: 2016-03-22
CPC Classification: F01D,F02C,F23R

Claim Text:
1. A midframe portion of a gas turbine engine, said midframe portion comprising: a compressor section with a last stage blade configured to orient an air flow discharged from the compressor section at a first angle; a turbine section with a first stage blade configured to receive the air flow oriented at a second angle; a manifold configured to directly couple the air flow from the compressor section to a combustor head of the gas turbine engine upstream of the turbine section; wherein the combustor head is within the manifold and configured to introduce an offset angle in the air flow from the first angle to the second angle such that the air flow discharged from the combustor head is oriented at the second angle; and wherein the combustor head is configured to at least maintain or augment the first angle of the air flow.