Heat shield for a gas turbine combustion chamber

Abstract

The present invention relates to a combustion chamber heat-shielding element of a gas-turbine, having a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall or a combustion chamber head, where the combustion chamber heat-shielding element is designed substantially plate-like and where on one side at least one bolt, which is designed as a separate component, is anchored on it by means of a bonded connection.

Claims

1. A combustion chamber heat-shielding arrangement of a gas-turbine, comprising: a combustion chamber heat-shielding element having a plate shape, a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall or a combustion chamber head, the bolt configured as a separate component from the combustion chamber heat-shielding element, the bolt having a first end having a non-cylindrical contoured base for anchoring to the combustion chamber heat-shielding element, a receptacle provided on the combustion chamber heat-shielding element, the receptacle including a non-cylindrical recess shaped for receiving the non-cylindrical contoured base of the first end of the bolt in a form fitting and rotational preventing locking manner, an adhesive bonded connection connecting the first end of the bolt to the non-cylindrical recess, the adhesive bonded connection consisting of the first end of the bolt, the non-cylindrical recess and an adhesive positioned between and connecting the first end of the bolt to the non-cylindrical recess, wherein the adhesive consists of a high-temperature resistant metal adhesive resistant to temperatures of at least 1000 C., wherein the receptacle includes effusion cooling holes.

2. The combustion chamber heat-shielding arrangement in accordance with claim 1, wherein the first end of the bolt is unthreaded.

3. The combustion chamber heat-shielding arrangement in accordance with claim 2, wherein the receptacle is one piece with the combustion chamber heat-shielding element.

4. The combustion chamber heat-shielding arrangement in accordance with claim 3, wherein the combustion chamber heat-shielding element is manufactured by an additive manufacturing method.

5. The combustion chamber heat-shielding arrangement in accordance with claim 2, wherein the combustion chamber heat-shielding element is at least one chosen from a combustion chamber tile and a heat shield.

6. The combustion chamber heat-shielding arrangement in accordance with claim 1, wherein the receptacle is one piece with the combustion chamber heat-shielding element.

7. The combustion chamber heat-shielding arrangement in accordance with claim 1, wherein the combustion chamber heat-shielding element is manufactured by an additive manufacturing method.

8. The combustion chamber heat-shielding arrangement in accordance with claim 1, wherein the combustion chamber heat-shielding element is at least one chosen from a combustion chamber tile and a heat shield.

Description

(1) The present invention is described in the following in light of the accompanying drawing, showing exemplary embodiments. In the drawing,

(2) FIG. 1 shows a schematic representation of a gas-turbine engine in accordance with the present invention,

(3) FIG. 2 shows a schematic (sectional) side view of a combustion chamber in accordance with the state of the art,

(4) FIG. 3 shows a top view and a side view of a combustion chamber tile known from the state of the art,

(5) FIG. 4 shows a sectional side view of a fastening possibility of a combustion chamber tile relative to the combustion chamber outer wall in accordance with the state of the art,

(6) FIG. 5 shows a simplified view of a heat shield for being used in the present invention with bolts and effusion cooling holes,

(7) FIG. 6 shows schematic side views and top views of differing embodiments of the bolt in accordance with the present invention,

(8) FIG. 7 shows side views and top views of differing embodiments of the combustion chamber heat-shielding element with receptacles in accordance with the present invention,

(9) FIG. 8 shows a representation of an exemplary embodiment with combustion chamber heat-shielding element and support towards the combustion chamber wall,

(10) FIG. 9 shows a view, by analogy with FIG. 8, with direct contact of the support on the combustion chamber wall,

(11) FIG. 10 shows schematic side views and top views of exemplary embodiments with effusion cooling holes, and

(12) FIGS. 11 and 12 show simplified side views, by analogy with FIGS. 8 and 9, with the bolt being secured by means of a locking pin.

(13) The gas-turbine engine 10 in accordance with FIG. 1 is an example of a turbomachine where the invention can be used. The following however makes clear that the invention can also be used in other turbomachines. The engine 10 is of conventional design and includes in the flow direction, one behind the other, an air inlet 11, a fan 12 rotating inside a casing, an intermediate-pressure compressor 13, a high-pressure compressor 14, combustion chambers 15, a high-pressure turbine 16, an intermediate-pressure turbine 17 and a low-pressure turbine 18 as well as an exhaust nozzle 19, all of which being arranged about a center engine axis 1.

(14) The intermediate-pressure compressor 13 and the high-pressure compressor 14 each include several stages, of which each has an arrangement extending in the circumferential direction of fixed and stationary guide vanes 20, generally referred to as stator vanes and projecting radially inwards from the engine casing 21 in an annular flow duct through the compressors 13, 14. The compressors furthermore have an arrangement of compressor rotor blades 22 which project radially outwards from a rotatable drum or disk 26 linked to hubs 27 of the high-pressure turbine 16 or the intermediate-pressure turbine 17, respectively.

(15) The turbine sections 16, 17, 18 have similar stages, including an arrangement of fixed stator vanes 23 projecting radially inwards from the casing 21 into the annular flow duct through the turbines 16, 17, 18, and a subsequent arrangement of turbine blades 24 projecting outwards from a rotatable hub 27. The compressor drum or compressor disk 26 and the blades 22 arranged thereon, as well as the turbine rotor hub 27 and the turbine rotor blades 24 arranged thereon rotate about the engine axis 1 during operation.

(16) FIG. 4 shows various side views according to the state of the art, illustrating a support 41 of the combustion chamber tile 34 relative to the combustion chamber wall 32. FIG. 5 shows a heat shield 42 according to the state of the art with bolts 38 and effusion cooling holes 37.

(17) FIG. 5 shows a heat shield according to the state of the art with bolts 38 and effusion cooling holes 37 and also with a centric recess for a fuel nozzle (see FIG. 2).

(18) FIG. 6 shows in the three left-hand representations schematic side views of exemplary embodiments of the bolt 38 in accordance with the invention. The right-hand half of FIG. 6 shows differing top views onto the bolt 38. Here, in particular, it can be seen that the bolt 38 can have a contoured base 48 which can be designed in a wide variety of forms, i.e. as a round flange, with rectangular projections, in polygonal form or in another embodiment.

(19) FIG. 7 shows in the left-hand half, in a schematic representation, simplified sectional views of exemplary embodiments of the combustion chamber heat-shielding element 34, 42 in accordance with the invention, and also of the receptacle 45 fastened thereon. The latter is provided with a recess 46 into which a contoured base 48 of the bolt 38 can be inserted and bonded. Like the combustion chamber heat-shielding element 34, 42, the receptacle 45 with the recess 46 can be manufactured in one piece with the combustion chamber heat-shielding element, for example by means of an additive manufacturing method, see above.

(20) The right-hand half of FIG. 7 shows in each case top views onto differing embodiments of the receptacle 45 or the associated recess 46. The lower-case letters a to f correspond here in each case to the side views and top views, respectively.

(21) FIGS. 8 and 9 show differing exemplary embodiments in accordance with the invention. According to FIG. 8, the combustion chamber heat-shielding element 34, 42 is kept at a distance from the combustion chamber wand 32 by means of supports 41. This creates a space between the receptacle 45 and the combustion chamber wall 32. In the exemplary embodiment of FIG. 9, the receptacle 45 is in direct contact with the combustion chamber wall 32.

(22) The reference numeral 44 shows in each case the bonded connection for anchoring the bolt 38 at the receptacle 45.

(23) FIG. 10 shows exemplary embodiments of effusion cooling holes 37 which in particular are designed adjacent to the receptacle 45 or provided directly inside the receptacle 45. The left-hand representations of FIG. 10 each show simplified sectional side views, while the right-hand half of FIG. 10 shows associated top views, as identified by the lower-case letters a to d.

(24) FIGS. 11 and 12 show a further design variant, by analogy with FIGS. 8 and 9, where the bolt 38 is not provided with a thread, but is held by means of a locking pin 47.

LIST OF REFERENCE NUMERALS

(25) 1 Engine axis 10 Gas-turbine engine 11 Air inlet 12 Fan rotating inside the casing 13 Intermediate-pressure compressor 14 High-pressure compressor 15 Combustion chamber 16 High-pressure turbine 17 Intermediate-pressure turbine 18 Low-pressure turbine 19 Exhaust nozzle 20 Guide vanes 21 Engine casing 22 Compressor rotor blades 23 Stator vanes 24 Turbine blades 26 Compressor drum or disk 27 Turbine rotor hub 28 Exhaust cone 29 Fuel nozzle 30 Combustion chamber outer casing 31 Combustion chamber inner casing 32 Combustion chamber wall 33 Turbine inlet guide vane row 34 Combustion chamber tile 35 Admixing hole 36 Inflow direction 37 Effusion cooling hole 38 Bolt 39 Nut 40 Combustion chamber head 41 Support 42 Heat shield 43 Thread 44 Bonded connection 45 Receptacle 46 Recess 47 Locking pin 48 Base