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Title: Method of making an aero-derivative gas turbine engine

Abstract

A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. A can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.

Inventors:
Publication Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1419776
Patent Number(s):
9,885,482
Application Number:
15/355,665
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2016 Nov 18
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Wiebe, David J. Method of making an aero-derivative gas turbine engine. United States: N. p., 2018. Web.
Wiebe, David J. Method of making an aero-derivative gas turbine engine. United States.
Wiebe, David J. Tue . "Method of making an aero-derivative gas turbine engine". United States. doi:. https://www.osti.gov/servlets/purl/1419776.
@article{osti_1419776,
title = {Method of making an aero-derivative gas turbine engine},
author = {Wiebe, David J.},
abstractNote = {A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. A can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Feb 06 00:00:00 EST 2018},
month = {Tue Feb 06 00:00:00 EST 2018}
}

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