BURNER SEAL OF A GAS TURBINE AND METHOD FOR MANUFACTURING THE SAME

Abstract

A burner seal of a gas turbine with a substantially tubular base body, which has a ring-shaped inlet lip on the inflow side and a funnel at its outflow side, wherein an inner diameter of the inflow side is embodied to be larger than an inner diameter of a sealing surface that is arranged axially in front of the funnel, wherein cooling channels are formed in the base body distributed about the circumference, wherein the cooling channels are formed respectively in the base body in the area of the sealing surface and of the funnel, and respectively open into an end area of the funnel in an exit hole.

Claims

1. A burner seal of a gas turbine comprising: a tubular base body including an inflow side and an outflow side; a ring-shaped inlet lip on the inflow side; a funnel on the outflow side; a sealing surface arranged axially upstream of the funnel, wherein an inner diameter of the inflow side is larger than an inner diameter of the sealing surface; an entry hole located in an inner surface of the burner seal; an exit hole positioned in the funnel; and a cooling channel formed in the base body and extending from the entry hole to the exit hole.

2. The burner seal according to claim 1, wherein the exit hole opens into an outermost end area of the funnel.

3. The burner seal according to claim 1, wherein a central axis of the exit hole is positioned at an angle of 70 to 90 with respect to a central axis of the burner seal.

4. The burner seal according to claim 1, wherein the entry hole is arranged in an area of the inner diameter of the inflow side.

5. The burner seal according to claim 1, wherein the entry hole is arranged in an area of the sealing surface.

6. The burner seal according to claim 1, wherein the cooling channel has at least one chosen from a circular, elliptic, diamond-shaped and drop-shaped cross section.

7. The burner seal according to claim 1, wherein a cross section of the cooling channel is variable along a length of the cooling channel.

8. The burner seal according to claim 1, wherein the cooling channel is at least one chosen from curved, bent and linear along a length of the cooling channel.

9. The burner seal according to claim 1, wherein a surface of the entry hole and a surface of the exit hole have same dimensions.

10. A method for manufacturing a burner seal, comprising: providing: a tubular base body including an inflow side and an outflow side; a ring-shaped inlet lip on the inflow side; a funnel on the outflow side; a sealing surface arranged axially upstream of the funnel, wherein an inner diameter of the inflow side is larger than an inner diameter of the sealing surface; an entry hole located in an inner surface of the burner seal; an exit hole positioned in the funnel; and a cooling channel formed in the base body and extending from the entry hole to the exit hole; manufacturing the burner seal using an additive process.

11. The burner seal according to claim 1, wherein a central axis of the exit hole is positioned at an angle of 70 to 80 with respect to a central axis of the burner seal.

12. The burner seal according to claim 11, wherein a central axis of the exit hole is positioned at an angle of 75 with respect to a central axis of the burner seal.

13. The burner seal according to claim 1, wherein a surface of the entry hole and a surface of the exit hole have different dimensions.

Description

[0028] In the following, the invention is explained based on exemplary embodiments in connection with the drawing. Herein:

[0029] FIG. 1 shows a gas turbine engine for using the gas turbine combustion chamber according to the invention,

[0030] FIG. 2 shows a simplified axial section view of a gas turbine combustion chamber according to the state of the art,

[0031] FIG. 3 shows an enlarged detailed view of the burner seal shown in FIG. 2,

[0032] FIG. 4 shows sectional views of different exemplary embodiments of the burner seal and the cooling channels in a rendering, which is analogous to FIG. 3,

[0033] FIG. 5 shows different embodiment variants in view A according to FIG. 4,

[0034] FIG. 6 shows different embodiment variants in view A or B according to FIG. 4,

[0035] FIG. 7 shows a partial sectional view of an exemplary embodiment according to the invention, which is analogous to FIG. 4,

[0036] FIGS. 8 and 9 show perspective views of different exemplary embodiments of the burner seal,

[0037] FIG. 10 shows a sectional view of a burner seal according to a particularly preferred exemplary embodiment of the invention,

[0038] FIG. 11a-11h show different exemplary embodiments of the burner seal with alternative embodiments of the cooling channel according to the particularly preferred exemplary embodiment of FIG. 10 and

[0039] FIG. 12 shows a partial sectional view of a burner seal according to a further preferred exemplary embodiment of the invention.

[0040] The gas turbine engine 110 according to FIG. 1 represents a general example of a turbomachine in which the invention may be used. The engine 110 is configured in a conventional manner and comprises, arranged successively in flow direction, an air inlet 111, a fan 112 that rotates inside a housing, a medium-pressure compressor 113, a high-pressure compressor 114, a combustion chamber 115, a high-pressure turbine 116, a medium-pressure turbine 117, and a low-pressure turbine 118 as well as an exhaust nozzle 119, which are all arranged around a central engine axis 101.

[0041] The medium-pressure compressor 113 and the high-pressure compressor 114 respectively comprise multiple stages, of which each has an arrangement of fixedly arranged stationary guide vanes 120 that extends in the circumferential direction, with the stationary guide vanes 120 being generally referred to as stator vanes and projecting radially inward from the core engine shroud 121 through the compressors 113, 114 into a ring-shaped flow channel. Further, the compressors have an arrangement of compressor rotor blades 122 that project radially outward from a rotatable drum or disc 125, and are coupled to hubs 126 of the high-pressure turbine 116 or the medium-pressure turbine 117.

[0042] The turbine sections 116, 117, 118 have similar stages, comprising an arrangement of stationary guide vanes 123 projecting radially inward from the housing 121 through the turbines 116, 117, 118 into the ring-shaped flow channel, and a subsequent arrangement of turbine blades/vanes 124 projecting outwards from the rotatable hub 126. During operation, the compressor drum or compressor disc 125 and the blades1 22 arranged thereon as well as the turbine rotor hub 126 and the turbine rotor blades/vanes 124 arranged thereon rotate around the engine central axis 101.

[0043] FIG. 4 shows different exemplary embodiments of the burner seal 6 according to the invention in a rendering analogous to FIG. 3. Here, it can in particular be seen that, adjacent to the area of larger inner diameters through which the cooling air flows in (see FIG. 3), an entry hole 20 of a cooling channel 22 is arranged in the axial direction in front of the sealing surface 16. The air flows out of the cooling channel 22 through an exit hole 21.

[0044] The different embodiment variants of FIG. 4 show that the exit hole 21 is respectively positioned at the side of the funnel 17 that is facing towards the combustion space. In this manner, the cooling air exits at the hot side of the funnel 17 and can be applied to the surface of the funnel as a cooling air film.

[0045] The exemplary embodiments of FIG. 4 show that the cooling channel 22 can be dimensioned in different manners and be formed differently with respect to its geometry. According to FIG. 4a, the cooling channel 22 is curved in an arc-shaped manner, FIG. 4b shows an s-shaped curvature similar to the embodiment according to FIG. 4c. According to FIG. 4d, the exit hole 21 is provided with an enlarged cross section. FIG. 4e shows a cross section of the cooling channel 22 that has a cavity 23 in its central area. According to FIG. 4f, the exit hole 21 is positioned at a radially exterior area of the funnel 17. FIG. 4g shows a stepped cross sectional shape of the cooling channel 22 that is comprised of linear components, while FIG. 4h shows an exemplary embodiment in which the cooling channel 22 is embodied in a coil-like manner to optimize the cooling of the burner seal 6 or of the funnel 17.

[0046] FIG. 4g shows views A and B, which FIGS. 5 and 6 are based on. FIG. 5a shows respectively round entry holes 20 to which courses of cooling channels 22 connect which are linear (FIG. 5a), obliquely positioned (FIG. 5b), arc-shaped (FIG. 5c), coiled (FIG. 5d), widened in the manner of diffusor (FIG. 5e) or provided with a cavity 23 (FIG. 5f).

[0047] In view A or view B, FIG. 6 shows possible embodiments of the entry hole 20 and the exit hole 21. They can be designed to be circular (FIG. 6a), oval (FIGS. 6b and 6c) or diamond-shaped (FIG. 6d).

[0048] By way of clarification, FIG. 7 shows a perspective partial sectional view of the burner seal according to the invention, from which in particular the arrangement of the entry hole 20, of the exit hole 21 as well as of the cooling channel 22 may be gathered.

[0049] FIGS. 8 and 9 respectively show perspective renderings of different embodiment variants, which differ in particular with respect to the embodiment and dimensioning of the entry hole 20 and of the exit hole 21.

[0050] FIGS. 10 to 12 show different variants of a particularly preferred embodiment of the present invention.

[0051] As shown in FIG. 10, the burner seal 6 seals with the sealing surface 16 at the fuel nozzle 5. The sealing surface 16 is formed with a smaller inner diameter than the area of the inflow side with the ring-shaped inlet lip 18 that is positioned in front of it in the flow direction.

[0052] Here, the entry holes 20 are provided in a manner distributed about the circumference at the transitional area between the inflow side and the sealing surface 16. Starting from the entry hole 20, the cooling channel 22 extends in the funnel 17 up to an outermost end area 17a of the funnel 17, and exits from the outermost end area 17a from an exit hole 21.

[0053] As can in particular be seen from FIG. 10, the outermost end area 17a of the funnel 17 is formed to be arc-shaped, in particular semi-circular, in its section. Here, the exit hole 21 is positioned in this arc-shaped, outermost end area 17a. As can be seen from FIG. 10, a central axis 24, which leads through a center point of the exit hole 21, is arranged at an angle to the main axis 25 of the burner seal 6. In the exemplary embodiment shown in FIG. 10, the angle is 75. In this manner, a particularly good air conduction of the cooling air through the funnel 17 as well as at the exit of the funnel can be achieved.

[0054] In particular the entire funnel 17 can be cooled at its side that is facing towards the combustion chamber, as well as at its side that is facing away from the combustion chamber. At that, the cooling channel 22 is guided through the funnel 17 in such a manner that a wall thickness towards the side that is facing towards the combustion chamber as well as the side that is facing away from the combustion chamber is identical. In this manner, a particular stability of the funnel is facilitated. A diameter of the cooling channel 22 tapers off in the flow direction. Thus, the cooling channel is formed as a nozzle.

[0055] In this way, the cooling channel can cool the sealing area 16 at which the burner seal 6 has contact with the fuel nozzle, as well as effectively cool the funnel 17 up to the end area 17a of the funnel.

[0056] FIGS. 11a to 11h show different variants for the shapes of the funnel. Here, it is shown that the cooling channel 22 can have most varied dimensions and geometries.

[0057] In FIG. 11a, the cooling channel is curved in an arc-shaped manner, wherein, starting from the entry hole 20, at first there is a linear area substantially parallel to the sealing surface 16, and after the curve a substantially linear area is provided again up to the outermost end area 17a of the funnel. The exit hole 21 is provided at the outermost tip of the funnel 17.

[0058] FIG. 11b shows an s-shaped curvature of the cooling channel 22, wherein the funnel 17 projects a little further into the combustion space.

[0059] FIG. 11c shows an embodiment that is similar to FIG. 11b, wherein the exit hole 21 is aligned at an angle of almost 90 with respect to the central axis 25 of the burner seal.

[0060] FIG. 11d shows an embodiment in which a cross section of the cooling channel 22 continuously tapers off starting from the entry hole 20 up to the exit hole 21.

[0061] FIG. 11e shows a cooling channel 22 that has a cavity 23 in a central area. In this manner, an improved cooling at the sealing surface 16 can be achieved.

[0062] FIG. 11f shows a cooling channel 22 in which a diameter of the entry hole 20 is smaller than a diameter of the exit hole 21. Thus, the cooling channel of FIG. 11f has a diffusor effect.

[0063] FIG. 11g shows a stepped cross-sectional shape of the cooling channel 22 that is comprised of linear components.

[0064] FIG. 11h shows a preferred embodiment, in which the cooling channel 22 is formed in a coil-like manner to optimize the cooling of the burner seal 6 of the funnel 17, in particular at the end of the burner seal 6 that is facing towards the combustion space.

[0065] FIG. 11g shows once more the views A and B in a schematic manner, wherein the geometric shape of entry holes 20 and the exit holes 21 is designed according to the examples shown in FIGS. 5 and 6. Here, any desired combination of different geometric shapes of entry holes 20 or exit holes 21 is possible.

[0066] FIG. 12 shows a further particularly preferred embodiment of the invention, which substantially corresponds to the embodiment shown in FIG. 10. In contrast to that, the outermost end area 17a is embodied in a linear manner in the preferred embodiment shown in FIG. 12. At that, the outermost end area 17a forms a surface E, which is parallel to the central axis 25 of the burner seal 6. The angle is exactly 90 in this exemplary embodiment.

[0067] Thus, the shown burner seal 6 of a gas turbine clearly provides an improvement of a cooling of the burner seal, which results in low wear and in particular also in low maintenance costs, since the burner seal 6 does not have to be replaced as often as in the state of the art. In addition, the solution according to the invention of providing the exit hole 21 at the end area 17a of the funnel 17 provides the possibility to cool the entire funnel. It can also be avoided that excessively hot areas occur at the funnel 17 at the side of the funnel that is facing towards the combustion chamber as well as at the side of the funnel that is facing away from the combustion chamber.

[0068] Alternatively, the present invention can also be described by the following phrases: [0069] 1. Burner seal of a gas turbine with a substantially tubular base body, which has a ring-shaped inlet lip on the inflow side (18) and a funnel (17) at its outflow side, wherein an inner diameter of the inflow side is embodied to be larger than an inner diameter of a sealing surface that is arranged axially in front of the funnel (16), wherein cooling channels (22) are formed in the base body in a manner distributed about the circumference, characterized in that the cooling channels (22) are respectively formed in the base body in the area of the sealing surface (16) and of the funnel (17), and respectively open into an exit hole (21) in an axially outwardly oriented area of the funnel (17). [0070] 2. Burner seal according to phrase 1, characterized in that the cooling channels (22) respectively have one entry hole (20) that is arranged in an area of the larger inner diameter of the base body. [0071] 3. Burner seal according to phrase 1 or 2, characterized in that the cooling channels (22) respectively have one entry hole (20) which is arranged in the sealing area (16). [0072] 4. Burner seal according to any of the phrases 1 to 3, characterized in that the exit hole (21) is formed on the external side of the funnel (17) for forming a cooling air film. [0073] 5. Burner seal according to any of the phrases 1 to 4, characterized in that the exit hole (21) is formed in the radially outwardly oriented direction out of the funnel (17) for forming a cooling air flow. [0074] 6. Burner seal according to any of the phrases 1 to 5, characterized in that the cooling channel (22) is provided with a circular, elliptic, diamond-shaped and/or drop-shaped cross section. [0075] 7. Burner seal according to any of the phrases 1 to 6, characterized in that the cross section of the cooling channel (22) is formed to be variable across its length. [0076] 8. Burner seal according to any of the phrases 1 to 7, characterized in that the cooling channel (22) is formed to be curved, bent and/or linear across its length. [0077] 9. Burner seal according to any of the phrases 1 to 8, characterized in that the surfaces of the entry hole (20) and of the exit hole (21) respectively have the same or different dimensions. [0078] 10. Method for manufacturing a burner seal (6) according to any of the phrases 1 to 9, wherein the method is an additive method.

PARTS LIST

[0079] 1 combustion chamber wall

[0080] 2 head plate

[0081] 3 heat shield

[0082] 4 combustion chamber head

[0083] 5 fuel nozzle

[0084] 6 burner seal

[0085] 7 shingle

[0086] 8 admixing hole

[0087] 9 cooling hole

[0088] 10 bolt

[0089] 11 nut

[0090] 12 impingement cooling hole

[0091] 13 effusion cooling hole

[0092] 14 cooling hole

[0093] 15 cooling air hole

[0094] 16 sealing surface

[0095] 17 funnel

[0096] 17a outermost end area of the funnel

[0097] 18 inlet lip

[0098] 19 annular web

[0099] 20 entry hole

[0100] 21 exit hole

[0101] 22 cooling channel

[0102] 23 cavity

[0103] 24 central axis

[0104] 25 central axis of the burner seal

[0105] angle between central axis 24 of the exit hole and central axis 25 of the burner seal

[0106] E surface of the outermost end area 17a

[0107] 101 engine central axis

[0108] 110 gas turbine engine/core engine

[0109] 111 air inlet

[0110] 112 fan

[0111] 113 medium-pressure compressor (compactor)

[0112] 114 high-pressure compressor

[0113] 115 combustion chamber

[0114] 116 high-pressure turbine

[0115] 117 medium-pressure turbine

[0116] 118 low-pressure turbine

[0117] 119 exhaust nozzle

[0118] 120 guide vanes

[0119] 121 core engine housing

[0120] 122 compressor rotor blades

[0121] 123 guide vanes

[0122] 124 turbine blades

[0123] 125 compressor drum or compressor disc

[0124] 126 turbine rotor hub

[0125] 127 outlet cone