Low cost annular combustor

Claim 2

An annular combustor for a gas turbine comprising: a bell-shaped housing defining an axis: an annular liner having inner and outer annular walls within said housing and spaced therefrom to define a radially outer compressed air inlet between said housing and said liner, an axially elongated compressed air annulus between said housing and said outer wall and a radially extending compressed air annulus in fluid communication with said axially elongated annulus oppositely of said inlet, said liner further including a generally axially facing annular outlet between said walls and just radially inward of said inlet; a typically circular fuel injection manifold in said axially elongated annulus and having a plurality of angularly spaced, generally axially directed openings through which fuel may flow; and a plurality of typically tubular nozzles extending through said outer wall to enter the space between said walls generally tangentially thereto, each said nozzle including an air inlet within said axially elongated annulus and a fuel inlet aligned with an associated one of said openings.

Claim 3

The annular combustor of claim 1 wherein said liner further includes a generally radial wall interconnecting said inner and outer walls opposite of said annular outlet.

Claim 4

The annular combustor of claim 2 further including a plurality of air openings in said outer wall adjacent said radial wall for directing compressed air in said axially elongated annulus into said liner and against said radial wall.

Claim 5

The annular combustor of claim 2 further including a plurality of air openings in said radial wall adjacent said inner wall for directing compressed air in said radial annulus into said liner and against said inner wall.

Claim 6

The annular combustor of claim 2 further including a plurality of first air openings in said outer wall adjacent said radial wall for directing compressed air in said axially elongated annulus into said liner and against said radial wall and a plurality of second air openings in said radial wall adjacent said inner wall for directing compressed air in said radial annulus into said liner and against said inner wall.

Claim 7

The annular combustor of claim 5 wherein said outer and radial walls are stamped sheet metal and said air openings are punched holes.

Claim 8

The annular combustor of claim 1 wherein said housing further includes a central sleeve within said inner wall to define a further axially elongated annulus in fluid communication with said radial annulus and opening just inside said annular outlet to provide for cooling of said inner wall and the introduction of dilution air at said annular outlet.

Claim 9

The annular combustor of claim 7 wherein said further axially elongated annulus is narrow in relation to said axially elongated annulus to increase the velocity of air flowing therethrough and thereby enhance heat transfer at said inner wall.

Claim 10

The annular combustor of claim 1 wherein said outer wall is formed of sheet metal and between said inlet and said nozzles includes a circumferential series of inwardly bent tabs directed toward said inlet to allow dilution air to enter said liner near said outlet.

Claim 11

An annular combustor for a gas turbine comprising: a bell-shaped housing having an axis; an axially extending sleeve within said housing; an annular liner within said housing and about said sleeve, said liner having concentric inner and outer, annular axially elongated walls respectively spaced from said sleeve and said housing and a radially extending end wall interconnecting said inner and outer walls at one end thereof; said housing, said sleeve and said inner, outer and end walls being formed of sheet metal; a circular fuel manifold with angularly spaced fuel dispensing openings and disposed between said housing and said outer wall and located in a first plane transverse to said axis; a plurality of open ended elongated tubes in said outer wall and adjacent said manifold, said tubes lying in a second plane parallel to said first plane and being directed generally tangential to the space between said inner and outer walls, one end of each tube being located in said space and the other end of each tube being located between said housing and said outer wall; there being one tube for each said fuel dispensing opening; and means establishing fluid communication between each fuel dispensing opening and the interior of its associated tube.

Claim 12

An annular combustor for a gas turbine comprising: a bell-shaped housing having an axis; an axially extending sleeve within said housing; an annular liner within said housing and about said sleeve, said liner having concentric inner and outer, annular axially elongated walls respectively spaced from said sleeve and said housing and a radially extending end wall interconnecting said inner and outer walls at one end thereof; said housing, said sleeve and said inner, outer and end walls being formed of sheet metal; a circular fuel manifold with angularly spaced fuel dispensing openings and disposed between said housing and said outer wall and located in a first plane transverse to said axis; a plurality of open ended elongated tubes in said outer wall and adjacent said manifold, said tubes lying in a second plane parallel to said first plane and being directed generally tangential to the space between said inner and outer walls, one end of each tube being located in said space and the other end of each tube being located between said housing and said outer wall; there being one tube for each said fuel dispensing opening; and means establishing fluid communication between each fuel dispensing opening and the interior of its associated tube.

Claim 13

The annular combustor of claim 10 wherein said manifold and said tubes are in side by side relation and said establishing means comprises a hole in the side of each tube and aligned with the associated fuel dispensing opening.

Claim 14

The annular combustor of claim 10 wherein said first plane is closer to said end wall than said second plane.

Claim 15

The annular combustor of claim 10 further including a fuel line extending to said fuel manifold, said fuel line being wholly between said housing and said outer wall.

Claim 16

The annular combustor of claim 10 further including a plurality of air openings in said outer wall adjacent said radial wall for directing compressed air in said housing into said liner and against said radial wall.

Claim 17

The annular combustor of claim 10 further including a plurality of air openings in said radial wall adjacent said inner wall for directing compressed air in said housing annulus into said liner and against said inner wall.

Claim 18

The annular combustor of claim 10 further including a plurality of first air openings in said outer wall adjacent said radial wall for directing compressed air in said housing into said liner and against said inner wall and a plurality of second air openings in said radial wall adjacent said inner wall for directing compressed air in said housing into said liner and against said inner wall.

Claim 19

The annular combustor of claim 10 wherein said outer and radial walls are stamped sheet metal and said air openings are punched holes.

Claim 20

An annular combustor for a gas turbine comprising: a bell-shaped housing having an axis; an axially extending sleeve within said housing; an annular liner within said housing and about said sleeve, said liner having concentric inner and outer, annular axially elongated walls respectively spaced from said sleeve and said housing and a radially extending end wall interconnecting said inner and outer walls at one end thereof; said housing, said sleeve and said inner, outer and end walls being formed of sheet metal; means for introducing fuel to be burned into said liner in a generally tangential direction at a plurality of circumferentially spaced locations; a first series of punched holes in said outer wall adjacent said radial wall to cause air to enter the liner and sweep as a film across said radial wall; and a second series of punched holes in said radial wall near said inner wall to allow air to enter the liner and flow in a film-like fashion along said inner wall.

Claim 21

An annular combustor for a gas turbine comprising: a bell-shaped housing having an axis; an axially extending sleeve within said housing; an annular liner within said housing and about said sleeve, said liner having concentric inner and outer, annular axially elongated walls respectively spaced from said sleeve and said housing and a radially extending end wall interconnecting said inner and outer walls at one end thereof; said housing, said sleeve and said inner, outer and end walls being formed of sheet metal; means for introducing fuel to be burned into said liner in a generally tangential direction at a plurality of circumferentially spaced locations; a first series of punched holes in said outer wall adjacent said radial wall to cause air to enter the liner and sweep as a film across said radial wall; and a second series of punched holes in said radial wall near said inner wall to allow air to enter the liner and flow in a film-like fashion along said inner wall.

Claim 22

The annular combustor of claim 18 wherein said sleeve and said inner wall are closely spaced to force air passing therethrough to flow at high velocity to thereby provide enhanced cooling of said inner wall.