US6094916A — Dry low oxides of nitrogen lean premix module for…

Claim 1

Independent Claim 95 words

A gas turbine engine, including: a combustor having at least one substantially can shape combustion chamber; a plurality of lean premix modules associated with each of said at least one combustion chamber, each of said modules having a centerline defining an axial direction and comprising a radial inflow swirler having a plurality of vanes oriented to accelerate a flow through said vanes; and at least one fueling pathway positioned axially along said radial swirler, said at least one fueling pathway includes a plurality of dispensing apertures adapted to dispense a fuel axially along said swirler.

Claim 2

Dependent Claim 95 words

A gas turbine engine, including: a combustor having at least one substantially can shape combustion chamber; a plurality of lean premix modules associated with each of said at least one combustion chamber, each of said modules having a centerline defining an axial direction and comprising a radial inflow swirler having a plurality of vanes oriented to accelerate a flow through said vanes; and at least one fueling pathway positioned axially along said radial swirler, said at least one fueling pathway includes a plurality of dispensing apertures adapted to dispense a fuel axially along said swirler.

Claim 3

Dependent Claim 19 words

The gas turbine engine in claim 1, wherein said plurality of lean premix modules number between seven and twenty-five.

Claim 4

Dependent Claim 17 words

The gas turbine engine in claim 2, wherein said plurality of lean premix modules number about twenty.

Claim 5

Dependent Claim 17 words

The gas turbine engine in claim 1, wherein said swirler is fixed relative to said premix module.

Claim 6

Dependent Claim 40 words

The gas turbine engine in claim 1, wherein said swirler has a hollow core extending between the vanes and along a length of the radial inflow swirler, wherein said hollow core defines a volume substantially free of any mechanical structure.

Claim 7

Dependent Claim 25 words

The gas turbine engine of claim 1, wherein said at least one substantially can shape combustion chamber defines at least one substantially cylindrical combustion chamber.

Claim 8

Dependent Claim 26 words

The gas turbine engine of claim 1, wherein said at least one substantially can shape combustion chamber defines a plurality of substantially can shape combustion chambers.

Claim 9

Dependent Claim 150 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustor having a dome, said combustor having a substantially can shape combustion chamber; and a plurality of lean premix modules positioned within said dome and in fluid communication with said substantially can shape combustion chamber, each of said modules having a centerline defining an axial direction, at least two of said centerlines not being coincident, each of said modules comprising: a radial inflow swirler fixed relative to said module and having an upstream end, an inlet, and a plurality of vanes oriented to accelerate a flow through said vanes; and a fueling pathway positioned axially along said radial swirler for delivering fuel across said swirler, said fueling pathway having a plurality of fuel passages located substantially at said inlet of said swirler for dispensing fuel axially along a length of said swirler inlet.

Claim 10

Dependent Claim 150 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustor having a dome, said combustor having a substantially can shape combustion chamber; and a plurality of lean premix modules positioned within said dome and in fluid communication with said substantially can shape combustion chamber, each of said modules having a centerline defining an axial direction, at least two of said centerlines not being coincident, each of said modules comprising: a radial inflow swirler fixed relative to said module and having an upstream end, an inlet, and a plurality of vanes oriented to accelerate a flow through said vanes; and a fueling pathway positioned axially along said radial swirler for delivering fuel across said swirler, said fueling pathway having a plurality of fuel passages located substantially at said inlet of said swirler for dispensing fuel axially along a length of said swirler inlet.

Claim 11

Dependent Claim 27 words

The combustor assembly in claim 8, wherein said plurality of fuel passages having fuel dispensing holes positioned generally radially inward and distributed axially along said fuel passages.

Claim 12

Dependent Claim 73 words

The combustor assembly in claim 9, wherein each of said fuel passages has a fore array of fuel dispensing holes having a positive angular orientation with respect to an upstream axial direction and measured from a line extending from said fuel passage to said centerline of said swirler and an aft array of fuel dispensing holes having a negative angular orientation with respect to the upstream axial direction and measured from said line.

Claim 13

Dependent Claim 22 words

The combustor assembly in claim 10, wherein said positive angular orientation is about 60° and said negative angular orientation is about 60°.

Claim 14

Dependent Claim 40 words

The combustor assembly in claim 8, wherein each of said vanes of said swirler has a leading edge and is inclined about 40° to a line extending from said leading edge of said vane to said centerline of said swirler.

Claim 15

Dependent Claim 17 words

The combustor assembly in claim 8, wherein said vanes of said radial swirler are flat and solid.

Claim 16

Dependent Claim 19 words

The combustor assembly in claim 8, wherein said substantially can shape combustion chamber defines a substantially cylindrical combustion chamber.

Claim 17

Dependent Claim 42 words

The combustor assembly in claim 8, wherein said combustor including a plurality of substantially can shape combustion chambers, and wherein each of said plurality of substantially can shape combustion chambers has a plurality of said lean premix modules in fluid communication therewith.

Claim 18

Dependent Claim 176 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustion housing having an upstream end; and a lean premix module connected to said upstream end of said combustion housing, said module having a centerline defining an axial direction and comprising: a radial inflow swirler fixed relative to said module and having an upstream end, an inlet, an outlet, and a plurality of vanes defining a plurality of flow channels therebetween, at least one of said channels having a varying cross-sectional width, said radial inflow swirler utilizing said plurality of vanes to swirl the fuel and air in one direction, each of said plurality of vanes has a trailing edge, and wherein said swirler defining between said trailing edges a hollow core extending substantially an entire axial length of said swirler and an entire radial length between said trailing edges; and a fueling pathway positioned axially along said swirler for delivering fuel across said swirler, said fueling pathway having an outlet located upstream of said outlet of said swirler.

Claim 19

Dependent Claim 176 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustion housing having an upstream end; and a lean premix module connected to said upstream end of said combustion housing, said module having a centerline defining an axial direction and comprising: a radial inflow swirler fixed relative to said module and having an upstream end, an inlet, an outlet, and a plurality of vanes defining a plurality of flow channels therebetween, at least one of said channels having a varying cross-sectional width, said radial inflow swirler utilizing said plurality of vanes to swirl the fuel and air in one direction, each of said plurality of vanes has a trailing edge, and wherein said swirler defining between said trailing edges a hollow core extending substantially an entire axial length of said swirler and an entire radial length between said trailing edges; and a fueling pathway positioned axially along said swirler for delivering fuel across said swirler, said fueling pathway having an outlet located upstream of said outlet of said swirler.

Claim 20

Dependent Claim 41 words

The combustor assembly in claim 16, wherein said fueling pathway includes a plurality of fuel passages, each of said fuel passages having a downstream side and fuel dispensing holes located on said downstream side and distributed axially along said fuel passages.

Claim 21

Dependent Claim 73 words

The combustor assembly in claim 17, wherein each of said fuel passages has a fore array of fuel dispensing holes having a positive angular orientation with respect to an upstream axial direction and measured from a line extending from said fuel passage to said centerline of said swirler and an aft array of fuel dispensing holes having a negative angular orientation with respect to the upstream axial direction and measured from said line.

Claim 22

Dependent Claim 57 words

The combustor assembly in claim 18, wherein each of said fuel passages has an axial midpoint; said fuel dispensing holes of said aft array are distributed substantially uniformly along each of said fuel passages; and said fuel dispensing holes of said fore array are distributed primarily downstream of said axial midpoint of each of said fuel passages.

Claim 23

Dependent Claim 24 words

The combustor assembly in claim 18, wherein said positive angular orientation is located about 60° and said negative angular orientation is located about 60°.

Claim 24

Dependent Claim 40 words

The combustor assembly in claim 16, wherein each of said vanes of said swirler has a leading edge and is inclined about 40° to a line extending from said leading edge of said vane to said centerline of said swirler.

Claim 25

Dependent Claim 17 words

The combustor assembly in claim 16, wherein said vanes of said radial swirler are flat and solid.

Claim 26

Dependent Claim 138 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustor having a dome; and a plurality of lean premix modules positioned within said dome, each of said modules having a centerline defining an axial direction and having a radial inflow swirler including a plurality of vanes with a swirler vane passageway between adjacent vanes that accelerates said fuel and said air, each of said plurality of vanes has a trailing edge, and wherein said swirler defining between diametrically opposed of said trailing edges a hollow core extending substantially an entire axial length of said swirler; and a plurality of fueling passageways positioned axially along said radial inflow swirler, and each of said swirler vane passageways has a corresponding one of said plurality of fueling passageways adapted to dispense fuel therein.

Claim 27

Dependent Claim 138 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustor having a dome; and a plurality of lean premix modules positioned within said dome, each of said modules having a centerline defining an axial direction and having a radial inflow swirler including a plurality of vanes with a swirler vane passageway between adjacent vanes that accelerates said fuel and said air, each of said plurality of vanes has a trailing edge, and wherein said swirler defining between diametrically opposed of said trailing edges a hollow core extending substantially an entire axial length of said swirler; and a plurality of fueling passageways positioned axially along said radial inflow swirler, and each of said swirler vane passageways has a corresponding one of said plurality of fueling passageways adapted to dispense fuel therein.

Claim 28

Dependent Claim 68 words

The combustor assembly in claim 23, wherein each of said lean premix modules further comprises a nozzle downstream of and in flow communication with said radial swirler, said nozzle having a converging section for accelerating the flow of mixed fuel and air to inhibit flashback into said module, and said nozzle having a diverging section downstream from said converging section for expanding the flow of fuel and air.

Claim 29

Dependent Claim 17 words

The combustor assembly in claim 24, wherein said converging section has an included angle of about 60°.

Claim 30

Dependent Claim 17 words

The combustor assembly in claim 24, wherein said diverging section has an included angle of about 70°.

Claim 31

Dependent Claim 130 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustion housing having an upstream end; and a premix module connected to said upstream end of said combustion housing, said module having a centerline defining an axial direction and having a radial inflow swirler including a plurality of vanes with a fluid flow passageway between adjacent vanes adapted to accelerate the fuel and air, each of said vanes has a trailing edge, and wherein said swirler defining between diametrically opposed of said trailing edges a hollow core extending substantially an entire axial length of said swirler; and a fueling pathway positioned axially along said radial inflow swirler, said pathway includes a plurality of dispensing holes adapted to dispense fuel therein along said swirler.

Claim 32

Dependent Claim 130 words

A combustor assembly for receiving fuel from an external source and air from a compressor, comprising: a combustion housing having an upstream end; and a premix module connected to said upstream end of said combustion housing, said module having a centerline defining an axial direction and having a radial inflow swirler including a plurality of vanes with a fluid flow passageway between adjacent vanes adapted to accelerate the fuel and air, each of said vanes has a trailing edge, and wherein said swirler defining between diametrically opposed of said trailing edges a hollow core extending substantially an entire axial length of said swirler; and a fueling pathway positioned axially along said radial inflow swirler, said pathway includes a plurality of dispensing holes adapted to dispense fuel therein along said swirler.

Claim 33

Dependent Claim 66 words

The combustor assembly in claim 27, wherein said lean premix module further comprises a nozzle downstream of and in flow communication with said radial swirler, said nozzle having a converging section for accelerating the flow of mixed fuel and air to inhibit flashback into said module, and said nozzle having a diverging section downstream from said converging section for expanding the flow of fuel and air.

Claim 34

Dependent Claim 17 words

The combustor assembly in claim 28, wherein said diverging section has an included angle of about 70°.

Claim 35

Dependent Claim 179 words

A combustor assembly for receiving a flow of fuel from an external source and a flow of air from a compressor, comprising: a combustor having a dome, said combustor having a substantially can shape combustion chamber; and a plurality of premix modules positioned within said dome and in flow communication with said substantially can shape combustion chamber, each of said modules having a centerline defining an axial direction and comprising: a radial inflow swirler having a inlet, an outlet, a downstream end, and a plurality of vanes with fluid flow passageways between said vanes, each of said plurality of vanes having a trailing edge; a plurality of fueling passageways extending axially along said radial inflow swirler, and each of said fluid flow passageways has at least one of said plurality of fueling passageways adapted to dispense fuel therein; and a premixing chamber connected to said downstream end of said radial swirler, said premising chamber having a substantially cylindrical shape with a diameter that is substantially the same as a distance between said trailing edges of diametrically opposed said vanes.

Claim 36

Dependent Claim 179 words

A combustor assembly for receiving a flow of fuel from an external source and a flow of air from a compressor, comprising: a combustor having a dome, said combustor having a substantially can shape combustion chamber; and a plurality of premix modules positioned within said dome and in flow communication with said substantially can shape combustion chamber, each of said modules having a centerline defining an axial direction and comprising: a radial inflow swirler having a inlet, an outlet, a downstream end, and a plurality of vanes with fluid flow passageways between said vanes, each of said plurality of vanes having a trailing edge; a plurality of fueling passageways extending axially along said radial inflow swirler, and each of said fluid flow passageways has at least one of said plurality of fueling passageways adapted to dispense fuel therein; and a premixing chamber connected to said downstream end of said radial swirler, said premising chamber having a substantially cylindrical shape with a diameter that is substantially the same as a distance between said trailing edges of diametrically opposed said vanes.

Claim 37

Dependent Claim 17 words

The combustor assembly in claim 30, wherein said radial swirler is fixed relative to said premix module.

Claim 38

Dependent Claim 41 words

The combustor assembly in claim 31, wherein each of said premix modules further includes a plurality of fuel tubes extending axially along said radial swirler and located adjacent said inlet of said swirler, each of said fuel tubes having an outlet.

Claim 39

Dependent Claim 44 words

The combustor assembly in claim 32, wherein each of said fuel tubes further includes a radially inward side; and said outlet of each of said fuel tubes further comprises a plurality of fuel holes located on said radially inward side of said fuel tube.

Claim 40

Dependent Claim 43 words

The combustor assembly in claim 30, wherein each of said premix modules further comprises a nozzle positioned downstream of and in flow communication with said premixing chamber, said nozzle having a converging section and a diverging section located downstream of said converging section.

Claim 41

Dependent Claim 17 words

The combustor assembly in claim 34, wherein said converging section has an included angle of about 60°.

Claim 42

Dependent Claim 17 words

The combustor assembly in claim 34, wherein said diverging section has an included angle of about 70°.

Claim 43

Dependent Claim 19 words

The combustor assembly of claim 30, wherein said substantially can shape combustion chamber defines a substantially cylindrical combustion chamber.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	2003-08-01	2004-01-31	2004-08-01	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	2007-08-01	2008-01-31	2008-08-01	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	2011-08-01	2012-01-31	2012-08-01	$7700.00	Window Closed / Lapsed

Dry low oxides of nitrogen lean premix module for industrial gas turbine engines

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