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Title: Swirling midframe flow for gas turbine engine having advanced transitions

Abstract

A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.

Inventors:
; ; ; ; ;
Publication Date:
Research Org.:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1337663
Patent Number(s):
9,528,706
Application Number:
14/105,313
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Dec 13
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

Citation Formats

Montgomery, Matthew D., Charron, Richard C., Rodriguez, Jose L., Kusters, Bernhard W., Morrison, Jay A., and Beeck, Alexander R. Swirling midframe flow for gas turbine engine having advanced transitions. United States: N. p., 2016. Web.
Montgomery, Matthew D., Charron, Richard C., Rodriguez, Jose L., Kusters, Bernhard W., Morrison, Jay A., & Beeck, Alexander R. Swirling midframe flow for gas turbine engine having advanced transitions. United States.
Montgomery, Matthew D., Charron, Richard C., Rodriguez, Jose L., Kusters, Bernhard W., Morrison, Jay A., and Beeck, Alexander R. Tue . "Swirling midframe flow for gas turbine engine having advanced transitions". United States. doi:. https://www.osti.gov/servlets/purl/1337663.
@article{osti_1337663,
title = {Swirling midframe flow for gas turbine engine having advanced transitions},
author = {Montgomery, Matthew D. and Charron, Richard C. and Rodriguez, Jose L. and Kusters, Bernhard W. and Morrison, Jay A. and Beeck, Alexander R.},
abstractNote = {A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Dec 27 00:00:00 EST 2016},
month = {Tue Dec 27 00:00:00 EST 2016}
}

Patent:

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