EP0169431A1 — Gas turbine combustor

Claim 1

Independent Claim 374 words

A gas turbine combustor (3) comprising ; an axially elongated inner casing(4)having an upstream side end providing thereon an end wall (21) provided with a plurality of air hole annularly arranged therein and a downstream side end for exhausting a combustion gas (7) led to gas turbine (2) blades, said inner casing (4)defining a head combustion chamber(11) on the upstreams side and a rear combustion chamber (12) on the downstream side and having a plurarilty of air holes (19) formed in the peripheral wall defining said head cmbustion chamber (11); an outer casing (5) so that an annular air passage is defined therebetween, and provided with an end cover (10)on the upstream side with a distance from said end wall (21) thereby providing an air passage communicating with said annular air passage ; a hollow frustoconical tubular member (13) coaxially disposed in said head combustion chamber (11) of said inner casing (4) so as to project into said head combustion chamber (11) from said end wall (21), said tubular member (13) having a conical surface defining annular combustion space in cooperation with said inner casing(4), said annular combustion space increasing in cross-sectional area from the upstream side toward the downstream side, said tubular member (13) having a plurality of fine cooling air holes (24) on the surface in said head combustion chamber and a closed end on the downstream side ; a fuel nozzle body, provided with a plurality of elongated fuel nozzles (22) annularly arranged, and secured to said end cover (10) so that said fuel nozzles (22) project into said annular combustion space through said air holes (24)of said end wall (21) so as to form gaps for air passage between said air holes (24) and said fuel nozzles (221 each of said fuel nozzles (22) having a fuel injection hole at its tip portion, said fuel injection holes being disposed in the vicinity of said air holes formed in said peripheral wall of said head combustion (11) on the upstream side; a plurality of air inlets(23)annularly provided on said inner casing (4) for substantially axially introducing air into said rear combustion chamber (12); and second stage combustion fuel nozzles provided for injection fuel into said air flows from said fuel inlets.

Claim 2

Dependent Claim 374 words

A gas turbine combustor (3) comprising ; an axially elongated inner casing(4)having an upstream side end providing thereon an end wall (21) provided with a plurality of air hole annularly arranged therein and a downstream side end for exhausting a combustion gas (7) led to gas turbine (2) blades, said inner casing (4)defining a head combustion chamber(11) on the upstreams side and a rear combustion chamber (12) on the downstream side and having a plurarilty of air holes (19) formed in the peripheral wall defining said head cmbustion chamber (11); an outer casing (5) so that an annular air passage is defined therebetween, and provided with an end cover (10)on the upstream side with a distance from said end wall (21) thereby providing an air passage communicating with said annular air passage ; a hollow frustoconical tubular member (13) coaxially disposed in said head combustion chamber (11) of said inner casing (4) so as to project into said head combustion chamber (11) from said end wall (21), said tubular member (13) having a conical surface defining annular combustion space in cooperation with said inner casing(4), said annular combustion space increasing in cross-sectional area from the upstream side toward the downstream side, said tubular member (13) having a plurality of fine cooling air holes (24) on the surface in said head combustion chamber and a closed end on the downstream side ; a fuel nozzle body, provided with a plurality of elongated fuel nozzles (22) annularly arranged, and secured to said end cover (10) so that said fuel nozzles (22) project into said annular combustion space through said air holes (24)of said end wall (21) so as to form gaps for air passage between said air holes (24) and said fuel nozzles (221 each of said fuel nozzles (22) having a fuel injection hole at its tip portion, said fuel injection holes being disposed in the vicinity of said air holes formed in said peripheral wall of said head combustion (11) on the upstream side; a plurality of air inlets(23)annularly provided on said inner casing (4) for substantially axially introducing air into said rear combustion chamber (12); and second stage combustion fuel nozzles provided for injection fuel into said air flows from said fuel inlets.

Claim 3

Dependent Claim 32 words

A gas turbine combustor(3)as defined in claim 1 wherein each of said fuel nozzles provided in said head combustion chamber 11 is opened nearly perpendicularly to the axis of said inner casing.

Claim 4

Dependent Claim 50 words

A gas turbine combustor (3) according to claim 1 wherein said air holes provided in the peripheral wall of said inner casing(4)are arranged in a plurality of row axially arranged with an interval therebetween, said rows having said air holes arranged annularly on the periphery of said inner (4) casing.

Claim 5

Dependent Claim 116 words

A gas turbine combustor(3)according to claim 3, wherein an axial position La of said air hole row on the most upstream side from said end wall (21) is within the range given as fcllows ; La = (0.6 ~1.7) x Lc , wherein Lc is a radial length corresponding to the difference in radius between said inner casing (4) and said tubular member (13) at said end wall (21), and wherein the length Lb of said tubular member (13) from said end wall(21) to the downstream end is within the following range : Lb = (2.0 - 5.20) x Lf wherein Lf is the position of said fuel injection holes most separated from said end (21),

Claim 6

Dependent Claim 77 words

A gas turbine combustor(3) according to claim 3, wherein the air supplied in said head combustion chamber (11) is in such ratios that the air is introduced in amounts of 8 % to 20 % through che air holes formed in said end wall (21), air is introduced in amounts of 10% to 23% through said most upstream side hole row, and air is introduced in amounts 57% to 82% through the remaining of said air holes.

Claim 7

Dependent Claim 30 words

A gas turbine combustor(3) according to claim 1, wherein said fuel nozzles in said head combustor(11) have dissimilar lengths to change the position for injecting fuel into said combustion chamber.

Claim 8

Dependent Claim 40 words

A gas turbine combustor(3) according to claim 1,. wherein said fuel nozzles projected ·in said head combustion chamber (11) are opened in the vicinity of said air hole row on the most upstream side so as to inject fuel thereabout.

Claim 9

Dependent Claim 224 words

A gas turbine combustor(3) comprising a head combustion chamber (11) in which fuel and air for a first stage combustion are introduced thereinto to burn, and a rear combustion chamber (12) in which fuel and air for a second stage combustion are introduced downstream of said head combustion chamber (11) and are burned, the improvement comprising : an inner tubular member (13) disposed coaxially of the axis of said head combustion chamber (11) to define an annular combustion space between said head combustion chamber (11) and said tubular member (13), said tubular member (13)having a front end on the downstream side and a plurality of fine holes for cooling air passage in the peripheral wall and said front end; a plurality of fuel nozzles arranged in said annular combustion space for supplying fuel for the first stage and opened more downstream than the upstream side end of said head combustion chamber (11) so as to subject the injected fuel to voltexes including both upward flows and downward flow thereby stabilizing flame resulting from said first stage combustion ; and a plurality of second stage nozzles provided close to the periphery of said rear combustion chamber(12)andmore downstream than said front end of said inner tubular member (13) for substantially axially injecting fuel for said second stage into the interior of said rear combustion chamber (12).

Claim 10

Dependent Claim 224 words

A gas turbine combustor(3) comprising a head combustion chamber (11) in which fuel and air for a first stage combustion are introduced thereinto to burn, and a rear combustion chamber (12) in which fuel and air for a second stage combustion are introduced downstream of said head combustion chamber (11) and are burned, the improvement comprising : an inner tubular member (13) disposed coaxially of the axis of said head combustion chamber (11) to define an annular combustion space between said head combustion chamber (11) and said tubular member (13), said tubular member (13)having a front end on the downstream side and a plurality of fine holes for cooling air passage in the peripheral wall and said front end; a plurality of fuel nozzles arranged in said annular combustion space for supplying fuel for the first stage and opened more downstream than the upstream side end of said head combustion chamber (11) so as to subject the injected fuel to voltexes including both upward flows and downward flow thereby stabilizing flame resulting from said first stage combustion ; and a plurality of second stage nozzles provided close to the periphery of said rear combustion chamber(12)andmore downstream than said front end of said inner tubular member (13) for substantially axially injecting fuel for said second stage into the interior of said rear combustion chamber (12).

Claim 11

Dependent Claim 46 words

A gas turbine combustor (3) according to claim 8, wherein each of said second stage fuel nozzles has a plurality of fuel injection holes at the tip portion, and said fuel injection holes are inserted between whirling vanes (37) forming air pathes of said second stage.

Claim 12

Dependent Claim 31 words

A gas turbine combustor(3)according to claim 9 wherein said whirling vanes(37)have openings in the direction in which the air is ejected nearly in parallel with the axial line of the combustor.

Claim 13

Dependent Claim 42 words

A gas turbine combustor (3)according to claim 8, wherein the length of said head combustion chamber(11) along the axial line thereof is greater, by 1.2 times but not more than 1.8 times, than the outer diameter of said head combustion chamber (11).

Claim 14

Dependent Claim 44 words

A gas turbine combustor(3)according to claim 9, wherein said whirling vanes (37) having portions in parallel to said second stage fuel nozzle (34)axis and portions inclined so as to form whirling air stream flowing substantially in parallel to the axis of said combustion chamber.

Claim 15

Dependent Claim 60 words

A gas turbine combustor(3)according to claim 9, wherein said whirling vanes(37)aresupported by a member defining said head and rear combustion chambers through resilient sealing members so that said whirling vanes (37) are free of the displacement of said member due to thermal expansion, and guide members are provided for guiding air to flow smoothly into between said whirling vanes (37).

Gas turbine combustor

Abstract

Inventors

Bibliographic Details

Claims Analysis

References Cited (Backward Citations)

USPTO Annuity & Maintenance Windows

Assigned Categories & Tags

Assign Category Tag