Turbomachine housing element

Abstract

A turbomachine housing element, having a flow channel for accommodating a rotor blade assembly and a first cavity at least partially produced by primary shaping; the first cavity being adapted for passive thermal insulation and/or the assemblable turbomachine housing element not being adapted for the active circulation of fluid through the first cavity; and/or, between the first cavity and the flow channel, a separate seal being attached to turbomachine housing element; and/or the first cavity extending in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at the level of the cavity and/or over a minimum axial length of the separate seal and/or being filled with air or a thermally insulating fluid, whose specific thermal conductivity λ is at least 10% lower than the specific thermal conductivity λ of air.

Claims

1. A turbomachine housing element for a compressor stage or turbine stage of a gas turbine, comprising: a flow channel for accommodating at least one rotor blade assembly; a first cavity at least partially produced in an additive manufacturing process; the first cavity being adapted for passive thermal insulation, the turbomachine housing element, when assembled in the compressor stage or turbine stage of the gas turbine, not being adapted for the active circulation of fluid through the first cavity, the first cavity being filled either with air or with a thermally insulating fluid, whose specific thermal conductivity λ is at least 10% lower than a specific thermal conductivity λ of air; and at least one further cavity produced at least partially by the additive manufacturing process, the at least one further cavity being adapted for passive thermal insulation, the turbomachine housing element, when assembled in the compressor stage or turbine stage of the gas turbine, not being adapted for active circulation of fluid through the at least one further cavity; wherein no channel extends from the first cavity to a surface of the housing machine element; and a separate seal between the flow channel and the at least one further cavity, the separate seal attached to the turbomachine housing element and sealing the at least one further cavity from the flow channel.

2. The turbomachine housing element as recited in claim 1, wherein the at least one further cavity extends in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at a level of the further cavity; or extends over a minimum axial length of the separate seal and is filled either with air or with the thermally insulating fluid or with another thermally insulating fluid whose specific thermal conductivity λ is at least 10% lower than the specific thermal conductivity λ of air.

3. The turbomachine housing element as recited in claim 1, wherein the at least one further cavity extends in axial direction of the flow channel over at least 50% of a minimal axial length of the turbomachine housing element at the level of this at least one further cavity and of a minimal axial length of the separate seal.

4. The turbomachine housing element as recited in claim 1 wherein the at least one further cavity numbers at most five further cavities.

5. The turbomachine housing element as recited in claim 1 wherein the turbomachine housing element is manufactured in one piece.

6. The turbomachine housing element as recited in claim 1 wherein the turbomachine housing element or the first cavity or the at least one further cavity is annularly shaped.

7. The turbomachine housing element as recited in claim 1 wherein the first cavity or the at least one further cavity are designed for passively adapting a thermal expansion of the turbomachine housing element to that of the rotor blade assembly.

8. A turbomachine comprising: said at least one turbomachine housing element as recited in claim 1, and said at least one rotor blade assembly accommodated in the flow channel.

9. A gas turbine comprising the turbomachine as recited in claim 8.

10. A compressor stage or turbine stage of a gas turbine comprising the turbomachine as recited in claim 8.

11. The turbomachine housing element as recited in claim 1 wherein, between the cavity and the flow channel, a separate seal is attached to the turbomachine housing element.

12. The turbomachine housing element as recited in claim 11 wherein the cavity extends in the axial direction of the flow channel over at least 20% of a minimum axial length of the separate seal.

13. A method for operating a turbomachine having the turbomachine housing element as recited in claim 1, the method comprising: passing fluid through the flow channel while the fluid is not actively circulated through the first cavity in any steady-state or transient operating condition.

14. The turbomachine housing element as recited in claim 1 wherein a volume of the first cavity and the at least one further cavity differ by at least 1% and at most 200%.

15. The turbomachine housing element as recited in claim 1 wherein the first cavity or the at least one further cavity extend in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at a level of the cavity or the at least one further cavity.

16. The turbomachine housing element as recited in claim 1 wherein the first cavity is filled with air.

17. The turbomachine housing element as recited in claim 1 wherein the at least one further cavity is filled with a thermally insulating fluid, whose specific thermal conductivity λ is at least 10% lower than a specific thermal conductivity λ of air.

18. A turbomachine housing element for a compressor stage or turbine stage of a gas turbine, comprising: a flow channel for accommodating at least one rotor blade assembly; a first cavity at least partially produced in an additive manufacturing process; the first cavity being adapted for passive thermal insulation, the turbomachine housing element, when assembled in the compressor stage or turbine stage of the gas turbine, not being adapted for the active circulation of fluid through the first cavity, the first cavity being filled either with air or with a thermally insulating fluid, whose specific thermal conductivity λ is at least 10% lower than a specific thermal conductivity λ of air; and at least one further cavity produced at least partially by the additive manufacturing process, the at least one further cavity being adapted for passive thermal insulation, the turbomachine housing element, when assembled in the compressor stage or turbine stage of the gas turbine, not being adapted for active circulation of fluid through the at least one further cavity, wherein no channel extends from the at least one further cavity to a surface of the turbomachine housing element; and a separate seal between the flow channel and the at least one further cavity, the separate seal attached to the turbomachine housing element and sealing the at least one further cavity from the flow channel.

19. The turbomachine housing element as recited in claim 1 wherein the at least one further cavity extends over a minimum axial length of the separate seal and is filled either with air or with the thermally insulating fluid or with another thermally insulating fluid whose specific thermal conductivity λ is at least 10% lower than the specific thermal conductivity λ of air.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Further advantageous embodiments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. To this end, the drawing shows, partly in schematic form, in:

(2) FIG. 1: a portion of a turbomachine having a turbomachine housing element in an embodiment of the present invention, in a meridional section;

(3) FIG. 2: a portion of a turbomachine having a turbomachine housing element in a further embodiment of the present invention in a view similar to that of FIG. 1; and

(4) FIG. 3: a portion of a turbomachine having a turbomachine housing element in a further embodiment of the present invention in a view similar to that of FIG. 1, 2.

(5) FIG. 4: a portion of a turbomachine having a turbomachine housing element in a further embodiment of the present invention in a view similar to that of FIG. 2, without channels.

DETAILED DESCRIPTION

(6) In an embodiment of the present invention, FIG. 1 shows a portion of a turbomachine having an installed turbomachine housing element 1 in a meridional section that contains an axial direction or the main machine axis of the turbomachine (horizontally in FIG. 1).

(7) Annularly shaped turbomachine housing element 1 has a flow channel 6 in which a rotor blade assembly 4 is accommodated.

(8) Turbomachine housing element 1 is manufactured in one piece in an additive manufacturing process and features an annularly shaped, co-manufactured first cavity 2.

(9) First cavity 2 is filled with air or a thermally insulating fluid whose specific thermal conductivity λ is at least 10% lower than specific thermal conductivity λ of air, air or thermally insulating fluid not being actively circulated through first cavity 2 in any steady-state or transient operating condition of the turbomachine; this cavity rather only being designed, adapted, used, or provided for passive thermal insulation.

(10) Between first cavity 2 and flow channel 6, a separate seal, especially an abradable liner and/or a honeycomb seal 3, is attached to turbomachine housing element 1.

(11) First cavity 2 extends in the axial direction of the flow channel (horizontally in FIG. 1) over approximately 85% of a minimum axial length of turbomachine housing element 1 at the level of cavity 2 and over approximately 70% of a minimum axial length of separate seal 3.

(12) In a further embodiment of the present invention, FIG. 2 shows a portion of a turbomachine having a turbomachine housing element 1 in a view similar to that of FIG. 1. Identical reference numerals identify corresponding features, so that reference is made to the preceding description, and the differences will be discussed below.

(13) In addition to first cavity 2, whose size, shape and configuration are adapted to the turbomachine housing element, in the embodiment of FIG. 2, turbomachine housing element has three further cavities 2′, 2″, 2′″ that are produced using the additive manufacturing process.

(14) As is first cavity 2, these further cavities 2′, 2″, 2′″ are also filled with air or a thermally insulating fluid whose specific thermal conductivity λ is at least 10% lower than specific thermal conductivity λ of air, air or thermally insulating fluid not being actively circulated through further cavities 2′, 2″, 2′″ in any steady-state or transient operating condition of the turbomachine; rather these cavities only being designed, adapted, used, or provided for passive thermal insulation.

(15) Further cavities 2′, 2″, 2′″ extend in the axial direction of flow channel 6 in each case over a substantial portion of the minimum axial length of turbomachine housing element 1 at the level of the specific cavity and the minimum axial length of separate seal 3.

(16) The volumes of at least two of cavities 2-2′″ differ by at least 10% and at most by 50%.

(17) Via one or a plurality of joint channels 5, each of whose minimum cross section is less than 10% of a minimum cross section of the smallest cavity that is traversable by flow, cavities 2-2′″ communicate with a surface of turbomachine housing element 1 that faces away (above in FIG. 2) from the flow channel.

(18) In the embodiment of FIG. 1, as well, one or more such channels extending from first cavity 2 to a surface of turbomachine housing element that faces away from the flow channel may be provided that are not discernible in the sectional view of FIG. 1.

(19) FIG. 3 shows a portion of a turbomachine having a turbomachine housing element 1 in accordance with a further embodiment of the present invention in a view that corresponds to that of FIG. 1, 2. Identical reference numerals identify corresponding features, so that reference is made to the preceding description, and the differences will be discussed below.

(20) In the embodiment of FIG. 3, differently contoured turbomachine housing element 1 only has a (first) cavity 2, as in the embodiment of FIG. 1, that communicates via one or more joint channels 5 with a surface (above in FIG. 3) of turbomachine housing element 1 that faces away from the flow channel.

(21) Although exemplary embodiments are explained in the preceding description, it should be noted that many modifications are possible.

(22) Thus, in a modification, first cavity 2 and/or further cavities 2′, 2″, 2′″ may each be sealed off, or the need for channels 5 is eliminated as shown in FIG. 4, in fact, in that, if indicated, to remove residual material remaining from the additive manufacturing process, passages used for the assemblable or finished turbomachine housing element are sealed. Accordingly, in the present case, a channel is understood, namely, to be a passage that is at least temporarily open or provided or specifically adapted for that purpose, in any case in the assemblable state or operation.

(23) It should be appreciated, moreover, that the exemplary embodiments are merely examples and are in no way intended to restrict the scope of protection, the uses or the design. Rather, the foregoing description provides one skilled in the art with a guideline for realizing at least one exemplary embodiment; various modifications being possible, particularly with regard to the function and location of the described components, without departing from the scope of protection as is derived from the claims and the combinations of features equivalent thereto.

REFERENCE NUMERAL LIST

(24) 1 turbomachine housing element 2 first cavity 2′, 2″, 2′″ further cavity 3 abradable liner/honeycomb seal (seal) 4 rotor blade assembly 5 channel 6 flow channel