Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D9/00—Stators
  • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
  • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
  • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
  • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
  • F02C3/145—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chamber being in the reverse flow-type
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/04—Air inlet arrangements
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
  • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/10—Stators
  • F05D2240/12—Fluid guiding means, e.g. vanes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/10—Stators
  • F05D2240/12—Fluid guiding means, e.g. vanes
  • F05D2240/126—Baffles or ribs
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/35—Combustors or associated equipment
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2250/00—Geometry
  • F05D2250/30—Arrangement of components
  • F05D2250/33—Arrangement of components symmetrical
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2250/00—Geometry
  • F05D2250/70—Shape
  • F05D2250/71—Shape curved
  • F05D2250/712—Shape curved concave

Definitions

• the subject matter disclosed herein relates generally to gas turbine engines and, more particularly, to a gas turbine engine including a compressor assembly with a splitter.
• At least some known gas turbine engines channel air through a compressor assembly and, more specifically, a compressor discharge casing (CDC) that encases an array of combustors.
• CDC compressor discharge casing
• the air is compressed between adjacent combustors, and vortices form along the meridional planes of the CDC.
• the compression of the air produces a local acceleration and weak diffusion air stream that may result in a low pressure recovery. Accordingly, a more efficient method and/or system for channeling air through the compressor assembly are desired.
• a method for assembling a gas turbine engine.
• the method includes providing a compressor discharge casing (CDC) including an annular wall that extends generally axially along at least a portion of the CDC.
• the CDC is coupled to a combustor casing such that a first combustor and a second combustor are housed within the annular wall.
• a splitter extends from the annular wall between the first and second combustors.
• the splitter includes a first surface that is configured to direct fluid towards the first combustor and a second surface that is configured to direct fluid towards the second combustor.
• a compressor assembly for use with a gas turbine engine.
• the compressor assembly includes a compressor discharge casing (CDC) including an annular wall that extends generally axially along at least a portion of the CDC.
• the CDC is configured to house a first combustor and a second combustor.
• a splitter extends from the annular wall between the first and second combustors.
• the splitter includes a first surface that is configured to direct fluid towards the first combustor and a second surface that is configured to direct fluid towards the second combustor.
• a gas turbine engine in yet another aspect, includes a first combustor, a second combustor, a compressor discharge casing (CDC), and a splitter.
• the CDC includes an annular wall that extends generally axially along at least a portion of the CDC.
• the CDC houses the first and second combustors.
• the splitter extends from the annular wall between the first and second combustors.
• the splitter includes a first surface that is configured to direct fluid towards the first combustor and a second surface that is configured to direct fluid towards the second combustor.
• FIG. 1 is an illustration of a side perspective of an exemplary gas turbine engine
• FIG. 2 is an illustration of a side perspective of an exemplary combustor that may be used with the gas turbine engine shown in FIG. 1;
• FIG. 3 is an illustration of a side perspective of an exemplary compressor discharge casing (CDC) that may be used with the gas turbine engine shown in FIG. 1 ; and
• FIG. 4 is an illustration of an end perspective of the CDC shown in FIG. 3.
• the methods and systems described herein facilitate improving a pressure recovery of a compressor discharge casing (CDC) by substantially aligning a fluid vortex about a longitudinal axis of a gas turbine engine.
• CDC compressor discharge casing
• FIG. 1 is an illustration of a side perspective of an exemplary gas turbine engine 100.
• gas turbine engine 100 includes, in serial flow arrangement, a compressor 102, a combustor assembly 104 including a plurality of combustors 106, and a turbine 108.
• Combustors 106 are spaced in an annular array extending about a shaft 110 that extends between and rotatably couples compressor 102 and turbine 108.
• FIG. 2 is an illustration of a side perspective of one combustor 106.
• compressor 102 includes a diffuser 112 defined therein.
• compressor 102 includes a compressor discharge casing (CDC) 114 including a compressor discharge plenum 116 defined therein.
• CDC compressor discharge casing
• combustor assembly 104 includes a combustor casing 118 that is coupled to CDC 114 via a fastener 120.
• combustor casing 118 extends about combustor assembly 104 and houses a plurality of fuel nozzle assemblies 122 and a combustor liner 124 including a combustion chamber 126 defined therein.
• combustor assembly 104 also includes a transition piece assembly 128. More specifically, in the exemplary embodiment, CDC 114 houses transition piece assembly 128 defining an annular passage 130 that extends between an inner wall 132 and an outer wall 134 of transition piece assembly 128. Inner wall 132 includes a guide cavity 136 defined therein. In one embodiment, inner wall 132 may be referred to as a transition piece, and outer wall 134 may be referred to as an impingement sleeve.
• inner wall 132 channels combustion gases generated in combustion chamber 126 downstream towards a turbine nozzle 138.
• outer wall 134 includes a plurality of openings 140 defined therein.
• turbine 108 drives compressor 102 via shaft 110.
• compressor 102 As compressor 102 is rotated, air is compressed as it flows downstream therethrough. Compressed air discharged from compressor 102 is channeled towards combustor 106, wherein the compressed air is mixed with fuel and ignited to generate combustion gases. More specifically, in the exemplary embodiment, compressor 102 discharges compressed air through diffuser 112 and compressor discharge plenum 116 towards combustor 106, as illustrated by the associated arrows. More specifically, in the exemplary embodiment, compressed air is discharged through compressor discharge plenum 116 and into annular passage 130 via openings 140.
• Compressed air entering annular passage 130 is directed into fuel nozzle assemblies 122, wherein the compressed air is mixed with fuel.
• the mixture is ignited within combustion chamber 126 to generate combustion gases.
• Combustion gases are discharged from combustion chamber 126 through guide cavity 136 and towards turbine nozzle 138.
• Turbine 108 converts the gas thermal energy of the combustion gases into mechanical rotational energy for use in rotating shaft 110.
• FIG. 3 is an illustration of a side perspective of CDC 114
• FIG. 4 is an illustration of an end perspective of CDC 114.
• CDC 114 includes a wall 142 that extends generally axially along at least a portion of CDC 114.
• wall 142 is coupled to combustor casing 118 via fastener 120.
• Wall 142 and combustor casing 118 house combustors 106 and, more specifically, a plurality of transition piece assemblies 128 therein.
• combustor casing 118 houses a first combustor surface 144 and a second combustor surface 146.
• combustor surfaces 144 and 146 may be referred as impingement sleeves.
• a splitter 148 extending from wall 142 facilitates improving the pressure recovery of CDC 114. More specifically, splitter 148 extends radially inward from an inner surface 150 of wall 142. Moreover, in the exemplary embodiment, splitter 148 extends substantially circumferentially between two adjacent transition piece assemblies 128, such as first and second combustor surfaces
• splitter 148 is positioned and/or spaced substantially equidistantly from first and second combustor surfaces 144 and 146 such that a distance 152 from a point on a first surface 154 to a point on first combustor surface 144 is approximately equal to a distance 156 from a corresponding point on a second surface 158 to a corresponding point on second combustor surface 146.
• splitter 148 may be positioned anywhere within CDC 114 that enables a desired air flow being formed, as described herein.
• first and second surfaces 154 and 158 are formed so that each is generally concave.
• first surface 154 and/or second surface 158 may be formed with any shape that enables a desired air flow to be formed.
• second surface 158 is displaced at an angle 160 from first surface 154 such that first surface 154 is oriented to direct fluid towards first combustor surface 144, and second surface 158 is oriented to direct fluid towards second combustor surface 146.
• first and second surfaces 154 and 158 are formed integrally with wall 142.
• splitter 148 may include a coupling surface (not shown) that is coupled to wall 142.
• First and second surfaces 154 and 158 extend generally axially along at least a portion of CDC 114.
• first surface 154 is coupled to second surface 158 at an apex 162 that extends axially along a portion of CDC 114.
• first surface 154 and/or second surface 158 may be coupled to a surface (not shown) extending between first surface 154 and second surface 158.
• first surface 154 is oriented in a mirrored relationship with respect to second surface 158 such that first and second surfaces 154 and 158 are substantially symmetrical about apex 162.
• first surface 154 and/or second surface 158 may be oriented in any non-symmetrical orientation that enables a desired air flow to be formed.
• compressed air is channeled through compressor discharge plenum
• Splitter 148 redirects a portion of the air flow within compressor discharge plenum 116 to facilitate increasing a circulation about an axis of gas turbine engine
• first surface 154 directs a first air flow towards first combustor surface 144
• second surface 158 directs a second air flow towards second combustor surface 146.
• first air flow circulates in a counterclockwise direction about the longitudinal axis and the second air flow circulates in a clockwise direction about the longitudinal axis. The separation of the first and second air flows facilitate reducing a cross communication of air flow between combustor surfaces 144 and 146.
• Exemplary embodiments of the compressor discharge casing and methods for assembling the compressor discharge casing are described above in detail.
• the methods and systems are not limited to the specific embodiments described herein, but rather, components of the methods and systems may be utilized independently and separately from other components described herein.
• the methods and systems described herein may have other industrial and/or consumer applications and are not limited to practice with gas turbine engines as described herein. Rather, the present invention can be implemented and utilized in connection with many other industries.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

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• 2010
  • 2010-04-15 US US12/761,073 patent/US8276390B2/en active Active
• 2011
  • 2011-03-30 WO PCT/US2011/030452 patent/WO2011130002A1/en not_active Ceased
  • 2011-03-30 JP JP2013504920A patent/JP5816264B2/ja active Active
  • 2011-04-12 EP EP11162104.1A patent/EP2378082B1/en active Active
  • 2011-04-15 CN CN201110104514.8A patent/CN102221002B/zh active Active

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