Staged low NOx premix gas turbine combustor

Claim 2

In a staged low NOx lean premix hot wall method for combusting fuel in a gas turbine combustor, the steps of: inducting a first lean premixture of fuel and compressed air into a first stage of a combustion chamber; igniting and combusting the inducted first premixture of fuel and air within the first stage of the combustion chamber to produce a stream of combustion products exiting the first stage of the combustion chamber; inducting a plurality of streams of a second premixture of fuel and compressed air into a second stage of the combustion chamber downstream of the first stage from generally opposite directions and colliding the streams in an impact region within the stream of combustion products exiting the first stage of the combustion chamber to produce a divergent intensely turbulent flow emanating from the impact region to define a Stirred Reactor region within the second stage of the combustion chamber; igniting and burning the second lean premixture of fuel and compressed air in the second stage of the hot wall combustion chamber to produce combustion products exiting the second stage of the combustion chamber; and maintaining the interior wall surface of the combustion chamber which faces the combustion flame at a temperature near the flame temperature within the combustor, whereby high stability low NOx operation is obtained over a wide range of turndown heat release values.

Claim 3

The method of claim 1 including the step of: directing the flow of combustion products exiting the Stirred Reactor region of the second stage of the combustion chamber to define a region of generally Plug Flow of combustion products within the second stage of the combustion chamber downstream of the Stirred Reactor region thereof.

Claim 4

The method of claim 1 wherein the step of inducting the first lean premixture of fuel and compressed air into the first stage of the combustion chamber includes the step of: directing the output flow of a plurality of separate premixers tangentially into an annular manifold at the end of the combustion chamber to produce a cyclonic flow of the premixture in the manifold; and inducting the cyclonic flow from the manifold into the first stage of the combustion chamber to provide a cyclonic flow of the lean premixture in the first stage of the combustion chamber.

Claim 5

The method of claim 1 wherein the fuel is natural gas consisting of a preponderance of methane.

Claim 6

The method of claim 1 including the step of recirculating the flow of combustion products within the first stage of the combustion chamber to define a zone of recirculation therein wherein the direction of flow is counter to the flow of the inducted first lean premixture.

Claim 7

The method of claim 1 wherein the colliding streams of inducted second lean premixture are collided generally head-on.

Claim 8

The method of claim 5 wherein the collided streams of inducted second lean premixture in the second stage are angled toward the upstream first combustion stage to flow a portion of the second premixture from the second stage into the recirculation zone of the first stage of the combustion chamber.

Claim 9

In a staged low NOx lean premix hot wall method for combusting fuel in a gas turbine combustor, the steps of: inducting a first lean premixture of fuel and compressed air into a first stage of a combustion chamber; igniting and combusting the inducted first premixture of fuel and air within the first stage of the combustion chamber to produce a stream of combustion products exiting the first stage of the combustion chamber; inducting a plurality of streams of a second premixture of fuel and compressed air to a second stage of the combustion chamber downstream of the first stage with a substantial component of velocity directed tangentially to the axis of revolution of the combustion chamber so as to induce a cyclonic flow of the second premixture in the second stage of the combustion chamber; igniting and burning the second lean premixture of fuel and compressed air in the second stage of the hot wall combustion chamber to produce combustion products exiting the second stage of the combustion chamber; and maintaining the interior surface of the wall of the combustion chamber which faces the combustion flame at a temperature near the flame temperature within the combustor, whereby low NOx emissions are obtained over a wide range of heat release values.

Claim 10

In a staged low NOx lean premix hot wall method for combusting fuel in a gas turbine combustor, the steps of: inducting a first lean premixture of fuel and compressed air into a first stage of a combustion chamber; igniting and combusting the inducted first premixture of fuel and air within the first stage of the combustion chamber to produce a stream of combustion products exiting the first stage of the combustion chamber; inducting a plurality of streams of a second premixture of fuel and compressed air to a second stage of the combustion chamber downstream of the first stage with a substantial component of velocity directed tangentially to the axis of revolution of the combustion chamber so as to induce a cyclonic flow of the second premixture in the second stage of the combustion chamber; igniting and burning the second lean premixture of fuel and compressed air in the second stage of the hot wall combustion chamber to produce combustion products exiting the second stage of the combustion chamber; and maintaining the interior surface of the wall of the combustion chamber which faces the combustion flame at a temperature near the flame temperature within the combustor, whereby low NOx emissions are obtained over a wide range of heat release values.

Claim 11

The method of claim 8 wherein the step of inducting the first lean premixture of fuel and compressed air into the first stage of the combustion chamber includes the step of: directing the output flow of a plurality of separate premixers tangentially into an annular manifold at the end of the combustion chamber to produce a cyclonic flow of the premixture in the manifold; and inducting the cyclonic flow from the manifold into the first stage of the combustion chamber to produce a cyclonic flow of the lean premixture in the first stage of the combustion chamber.

Claim 12

The method of claim 9 wherein the first and second premixtures are inducted into the first and second stages of the combustion chamber so as to produce counter-rotating first and second cyclonic flow patterns in the first and second stages of the combustion chamber.

Claim 13

In a staged low NOx lean premix hot wall gas turbine combustor having a combustion chamber with first and second stage regions: first inducting means for inducting a first lean premixture of fuel and compressed air into the first stage of the combustion chamber; igniter means for igniting and combusting the inducted first premixture of fuel and air within the first stage of the combustion chamber to produce a stream of combustion products exiting the first stage of the combustion chamber; second inducting means for inducting a plurality of streams of a second premixture of fuel and compressed air into the second stage of the combustion chamber downstream of the first stage from generally opposite directions and colliding the streams in an impact region within the stream of combustion products exiting the first stage of the combustion chamber to produce a divergent intensely turbulent flow emanating from the impact region to define a Stirred Reactor region within the second stage of the combustion chamber within which the second lean premixture of fuel and compressed air is ignited and burned to produce combustion products exiting the second stage of the combustion chamber; and thermal insulation means for maintaining the interior wall surface of the combustion chamber which faces the combustion flame at a temperature near the flame temperature within the combustor, whereby high stability low NOx operation is obtained over a wide range of turndown heat release values.

Claim 14

In a staged low NOx lean premix hot wall gas turbine combustor having a combustion chamber with first and second stage regions: first inducting means for inducting a first lean premixture of fuel and compressed air into the first stage of the combustion chamber; igniter means for igniting and combusting the inducted first premixture of fuel and air within the first stage of the combustion chamber to produce a stream of combustion products exiting the first stage of the combustion chamber; second inducting means for inducting a plurality of streams of a second premixture of fuel and compressed air into the second stage of the combustion chamber downstream of the first stage from generally opposite directions and colliding the streams in an impact region within the stream of combustion products exiting the first stage of the combustion chamber to produce a divergent intensely turbulent flow emanating from the impact region to define a Stirred Reactor region within the second stage of the combustion chamber within which the second lean premixture of fuel and compressed air is ignited and burned to produce combustion products exiting the second stage of the combustion chamber; and thermal insulation means for maintaining the interior wall surface of the combustion chamber which faces the combustion flame at a temperature near the flame temperature within the combustor, whereby high stability low NOx operation is obtained over a wide range of turndown heat release values.

Claim 15

The combustor of claim 11 including: Plug Flow means for directing the flow of combustion products exiting the Stirred Reactor region of the second stage of the combustion chamber to define a region of generally Plug Flow of combustion products within the second stage of the combustion chamber downstream of the Stirred Reactor region thereof.

Claim 16

The combustor of claim 11 wherein said first inducting means includes: directing means for directing the output flow of a plurality of separate premixers tangentially into an annular region at the end of the combustion chamber to produce a cyclonic flow of the premixture in the annular region; and throat means for inducting the cyclonic flow from said annular region into the first stage of the combustion chamber to provide a cyclonic flow of the lean premixture in the first stage of the combustion chamber.

Claim 17

The combustor of claim 11 wherein the fuel is natural gas consisting of a preponderance of methane.

Claim 18

The combustor of claim 11 including recirculating means for recirculating the flow of combustion products within the first stage of the combustion chamber to define a zone of recirculation therein wherein the direction of flow is counter to the flow of the inducted first lean premixture.

Claim 19

The combustor of claim 11 wherein the colliding streams of inducted second lean premixture are collided generally head-on.

Claim 20

The combustor of claim 15 wherein said recirculating means includes directing means for angling the collided streams of inducted second lean premixture in the second stage toward the upstream first combustion stage to flow a portion of the second premixture from the second stage into the recirculation zone of the first stage of the combustion chamber.

Claim 21

In a staged low NOx lean premix hot wall gas turbine combustor having a combustion chamber with an axis revolution and first and second combustion stages: first stage inducting means for inducting a first lean premixture of fuel and compressed air into the first stage of the combustion chamber; igniter means for igniting and combusting the inducted first premixture of fuel and air within the first stage of the combustion chamber to produce a stream of combustion products exiting the first stage of the combustion chamber; second stage inducting means for inducting a plurality of streams of a second premixture of fuel and compressed air into the second stage of the combustion chamber downstream of the first stage with a substantial component of velocity directed tangentially to the axis of revolution of the combustion chamber so as to induce a cyclonic flow of the second premixture in the second stage of the combustion chamber for burning the second lean premixture of fuel and compressed air in the second stage of the hot wall combustion chamber to produce combustion products exiting the second stage of the combustion chamber; and thermal insulation means for maintaining the interior surface of the wall of the combustion chamber which faces the combustion flame at a temperature near the flame temperature within the combustor, whereby low NOx emissions are obtained over a wide range of heat release values.

Claim 22

In a staged low NOx lean premix hot wall gas turbine combustor having a combustion chamber with an axis revolution and first and second combustion stages: first stage inducting means for inducting a first lean premixture of fuel and compressed air into the first stage of the combustion chamber; igniter means for igniting and combusting the inducted first premixture of fuel and air within the first stage of the combustion chamber to produce a stream of combustion products exiting the first stage of the combustion chamber; second stage inducting means for inducting a plurality of streams of a second premixture of fuel and compressed air into the second stage of the combustion chamber downstream of the first stage with a substantial component of velocity directed tangentially to the axis of revolution of the combustion chamber so as to induce a cyclonic flow of the second premixture in the second stage of the combustion chamber for burning the second lean premixture of fuel and compressed air in the second stage of the hot wall combustion chamber to produce combustion products exiting the second stage of the combustion chamber; and thermal insulation means for maintaining the interior surface of the wall of the combustion chamber which faces the combustion flame at a temperature near the flame temperature within the combustor, whereby low NOx emissions are obtained over a wide range of heat release values.

Claim 23

The combustor of claim 18 wherein said first stage inducting means includes: an annular manifold at the end of the combustion chamber; directing means for directing the output flow of a plurality of separate premixers tangentially into said annular manifold to produce a cyclonic flow of the premixture in the manifold; and throat means for inducting the cyclonic flow from said manifold into the first stage of the combustion chamber to produce a cyclonic flow of the lean premixture in the first stage of the combustion chamber.

Claim 24

The combustor of claim 19 wherein said first and second inducting means induct said premixtures into the first and second stages of the combustion chamber so as to produce counter-rotating first and second cyclonic flow patterns in the first and second stages of the combustion chamber.