skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: Gas flow path for a gas turbine engine

Abstract

A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.

Inventors:
; ; ; ; ;
Publication Date:
Research Org.:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1346959
Patent Number(s):
9,593,853
Application Number:
14/185,352
Assignee:
SIEMENS ENERGY, INC. NETL
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2014 Feb 20
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

Citation Formats

Montgomery, Matthew D., Charron, Richard C., Snyder, Gary D., Pankey, William W., Mayer, Clinton A., and Hettinger, Benjamin G. Gas flow path for a gas turbine engine. United States: N. p., 2017. Web.
Montgomery, Matthew D., Charron, Richard C., Snyder, Gary D., Pankey, William W., Mayer, Clinton A., & Hettinger, Benjamin G. Gas flow path for a gas turbine engine. United States.
Montgomery, Matthew D., Charron, Richard C., Snyder, Gary D., Pankey, William W., Mayer, Clinton A., and Hettinger, Benjamin G. Tue . "Gas flow path for a gas turbine engine". United States. doi:. https://www.osti.gov/servlets/purl/1346959.
@article{osti_1346959,
title = {Gas flow path for a gas turbine engine},
author = {Montgomery, Matthew D. and Charron, Richard C. and Snyder, Gary D. and Pankey, William W. and Mayer, Clinton A. and Hettinger, Benjamin G.},
abstractNote = {A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Mar 14 00:00:00 EDT 2017},
month = {Tue Mar 14 00:00:00 EDT 2017}
}

Patent:

Save / Share:
  • This patent describes an arcuate duct segment for an axial flow gas turbine engine, the engine having a high pressure turbine, a low pressure turbine and a transition region extending between the turbines. The segment has an axis of radius R/sub 1/, a convex side and a concave side disposed about the axis, the concave side adapting the duct segment to bound the transition region. The segment comprises: a first foot which extends circumferentially about the convex side of the segment, which is radially oriented with respect to the axis R/sub 1/, and which has a radial length R/sub f1/more » from the concave side; a second foot which extends circumferentially about the convex side of the segment, which is radially oriented with respect to the axis R/sub 1/, which has a radial length R/sub f2/ from the concave side and which is spaced axially from the first foot by a first distance D/sub 1/; and a transition piece having the concave side which is angled with respect to the axis of the segment, which has a span extending between the first foot and the second foot for joining the first foot to the second foot and which has an extension projecting from the first foot in cantilevered fashion and extending a second distance D/sub 2/ from the first foot.« less
  • This patent describes a gas turbine engine, the method for ejecting foreign matter from the core flow path into the bypass flow path. It comprises providing a scoop slidably mounted in a block between the core flow path and the bypass flow path; providing an activator mechanism for repositioning the scoop; and activating the activator mechanism at low power levels to protrude the scoop into the core flow path and to cause ice and debris which otherwise exist in the core flow path to be ejected from the core flow path into the bypass flow path.
  • A method of forming a nonlinear dual fuel path stem for a gas turbine engine is described comprising the steps of: (a) providing a substantially linear generally tube shaped integral first member for carrying a first fuel flow, the first member having an input end and an output end; (b) providing a substantially linear generally tube shaped integral second member for carrying a second fuel flow, the second member having an input end and an output end; (c) providing a substantially linear structural integral third member, the third member having an input end and an output end; (d) disposing themore » first and second members within the third member wherein the input ends of the first and second members are located within the input end of the third member and the output ends of the first and second members are located within the output end of the third member; (e) providing space means for reducing contact between the second member and the third member while providing structural support and an insulating space between the second and third members, and then, (f) bending the third member to cause the first and second fuel flows to be nonlinear.« less
  • A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the airmore » flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).« less
  • A transition duct system (100) for routing a gas flow from a combustor (102) to the first stage (104) of a turbine section (106) in a combustion turbine engine (108), wherein the transition duct system (100) includes one or more converging flow joint inserts (120) forming a trailing edge (122) at an intersection (124) between adjacent transition ducts (126, 128) is disclosed. The transition duct system (100) may include a transition duct (126, 128) having an internal passage (130) extending between an inlet (132, 184) to an outlet (134, 186) and may expel gases into the first stage turbine (104)more » with a tangential component. The converging flow joint insert (120) may be contained within a converging flow joint insert receiver (136) and disconnected from the transition duct bodies (126, 128) by which the converging flow joint insert (120) is positioned. Being disconnected eliminates stress formation within the converging flow joint insert (120), thereby enhancing the life of the insert. The converging flow joint insert (120) may be removable such that the insert (120) can be replaced once worn beyond design limits.« less