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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

Abstract

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).

Inventors:
Publication Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1461514
Patent Number(s):
10,012,098
Application Number:
13/407,987
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Feb 29
Country of Publication:
United States
Language:
English

Citation Formats

Rodriguez, Jose L. 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. United States: N. p., 2018. Web.
Rodriguez, Jose L. 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. United States.
Rodriguez, Jose L. Tue . "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". United States. https://www.osti.gov/servlets/purl/1461514.
@article{osti_1461514,
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},
author = {Rodriguez, Jose L.},
abstractNote = {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).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {7}
}

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