W501D5/D5A DF42 combustion system

Patent metadata

Field	Value
Publication number	US-10982853-B2
Application number	US-201916280173-A
Country	US
Kind code	B2
Filing date	Feb 20, 2019
Priority date	Dec 12, 2013
Publication date	Apr 20, 2021
Grant date	Apr 20, 2021

Abstract

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

First claim

What is claimed is:

1. A gas turbine engine comprising;
a compressor section;
a plurality of fuel nozzles in a combustion section, said fuel nozzles providing fuel for combustion, where each of said fuel nozzles includes one or more fluid atomizing device with orifices configured to dispense liquid fuel and water in different atomized spray patterns and an integral heat shielding device;
a plurality of combustors in the combustion section, each of said combustors receiving the fuel from one of the fuel nozzles and burning the fuel, where each of said combustors includes a combustor basket and a slip-joint cross-flame duct for connecting adjacent combustors;
a plurality of transition components in the combustion section, each of said transition components receiving combustion gases from one of the combustors and delivering the combustion gases to a turbine section; and
the turbine section including a plurality of rotor assemblies, where each rotor assembly includes a rotor disk and a plurality of turbine blades, wherein
each combustor basket includes a basket liner having an input end receiving air and fuel output end through which a hot working gas exits the combustor basket, said combustor basket further including a double-wall exit cone positioned within the basket liner and coupled to the basket liner upstream of the basket exit, said double-wall exit cone including an inner cone wall and an outer cone wall defining an annular exit cone channel therebetween, each of the inner cone wall and the outer cone wall including an inner surface and an outer surface, where the outer surface of the inner cone wall and the inner surface of the outer cone wall face the annular exit cone channel, said combustor basket further including a splash plate mounted to the outer cone wall and extending parallel to the output end of the basket liner so as to define an annular splash plate channel therebetween, wherein the outer cone wall is attached to the basket so as to allow a cooling air to be split between the double-wall exit cone and the splash plate,
a plurality of pairs of adjacent cooling fluid feed holes provided through the basket liner and circumferentially disposed around the output end of the basket liner so that one of the feed holes in each of the plurality of pairs of adjacent cooling fluid feed holes is in fluid communication annular exit cone channel and is prevented from being in fluid communication with the annular splash plate channel and an other feed hole in each of the plurality of pairs of adjacent cooling fluid feed soles is in fluid communication with the annular splash plate channel and is prevented from being in fluid communication with the annular exit cone channel.

2. The gas turbine engine of claim 1 wherein each of the combustors includes:
at least one platefin cooling system formed from a platefin member positioned radially inward from an inner surface of the basket liner;
at least one first rib section which extends between the platefin member and the combustor basket, thereby separating a first cooling circuit from a second cooling circuit,
wherein the first cooling circuit is upstream from the second cooling circuit; wherein the first cooling circuit includes at least one first outlet positioned in the platefin member upstream from the at least one first rib section; and
wherein the second cooling circuit includes at least one second outlet positioned downstream from the at least one first rib section.

3. The gas turbine engine of claim 1 wherein the slip-joint cross-flame duct comprises:
a first duct extending along a longitudinal axis and configured to be coupled to a first combustor of the plurality of combustors, the first duct comprising:
a first outer sleeve having a first end configured to be coupled to the first combustor and a second end on an opposite end from the first end, and
a first inner housing positioned within the first outer sleeve and having a first end adjacent the first combustor and a second end extending from the second end of the first outer sleeve;

a first cooling chamber positioned between an outer surface of the first inner housing and an inner surface of the first outer sleeve;
a second duct extending along the longitudinal axis and configured to be coupled to a second combustor of the plurality of combustors, wherein the second duct is configured to slidably receive the first duct, the second duct comprising:
a second outer sleeve having a first end configured to be coupled to the second combustor and extending toward the first duct to slidably receive the second end of the first inner housing within a second end of the second outer sleeve, and
a second inner housing positioned within the second outer sleeve and having a first end adjacent the second combustor and a second end extending toward the second end of the second outer sleeve; and

a second cooling chamber positioned between an outer surface of the second inner housing and an inner surface of the second outer sleeve.

4. The gas turbine engine of claim 1 wherein each of the transition components includes a first end mounted to one of the combustors and receiving the combustion gases, a second end opposite to the first end outputting the combustion gases, and a transition section between the first end and the second end having an outer wall defining a chamber therein through which the combustion gases flow, said outer wall having an inside surface and an outside surface, said transition section including a plurality of first effusion cooling holes extending through the outer wall and being angled in a direction so that an end of the effusion cooling holes at the inside surface is farther upstream relative to a flow of the combustion gases than an end of the effusion cooling holes at the outside surface.

5. The gas turbine engine of claim 1 wherein each of the transition components includes a transition cylinder at a first end mounted to one of the combustors and receiving the combustion gases, where the transition cylinder includes a plurality of circumferential or longitudinal slots on an outer surface, and a cylindrical sleeve fitted over the circumferential or longitudinal slots of the transition cylinder to form a plurality of circumferential or longitudinal cooling channels, and the cylindrical sleeve includes a cooling air inlet hole aligned with each of the slots to allow cooling air to enter and pass through the circumferential or longitudinal cooling channels.

Assignees

• Siemens Energy Inc

Inventors

• Polyzopoulos Charalambos
• Thackway Richard L
• Ramier Stephen A
• Barve Vinayak V
• Abou-Jaoude Khalil Farid
• Garan Daniel W
• Holzapfel David P
• Spence Kevin J
• Markovitz Joseph Scott
• Cotten Blake R
• Dave Urmi B
• Krishnan Vaidyanathan
• Escandon Michael C

Classifications

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R3/36

  Supply of different fuels · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05B2240/40

  Use of a multiplicity of similar components · CPC title