Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section

Rodriguez, Jose L.

Title: Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section

Patent · Tue Jul 03 00:00:00 EDT 2018

OSTI ID:1461514

Rodriguez, Jose L.

A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).

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Research Organization:: Siemens Energy, Inc., Orlando, FL (United States)

Sponsoring Organization:: USDOE

DOE Contract Number:: FC26-05NT42644

Assignee:: Siemens Energy, Inc. (Orlando, FL)

Patent Number(s):: 10,012,098

Application Number:: 13/407,987

OSTI ID:: 1461514

Resource Relation:: Patent File Date: 2012 Feb 29

Country of Publication:: United States

Language:: English

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