EP4069947A1 - Dichtungsträger für eine turbomaschine mit schlitzartigen öffnungen im dichtungskörper - Google Patents
Dichtungsträger für eine turbomaschine mit schlitzartigen öffnungen im dichtungskörperInfo
- Publication number
- EP4069947A1 EP4069947A1 EP20845675.6A EP20845675A EP4069947A1 EP 4069947 A1 EP4069947 A1 EP 4069947A1 EP 20845675 A EP20845675 A EP 20845675A EP 4069947 A1 EP4069947 A1 EP 4069947A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- slot
- sealing body
- openings
- seal carrier
- cavities
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000013016 damping Methods 0.000 claims abstract description 23
- 238000007789 sealing Methods 0.000 claims description 56
- 239000012530 fluid Substances 0.000 claims description 18
- 238000004891 communication Methods 0.000 claims description 5
- 238000005192 partition Methods 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 17
- 230000000694 effects Effects 0.000 description 6
- 239000000969 carrier Substances 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000000654 additive Substances 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 2
- 230000004323 axial length Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000003313 weakening effect Effects 0.000 description 2
- 238000012790 confirmation Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000009760 electrical discharge machining Methods 0.000 description 1
- 239000011796 hollow space material Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000011218 segmentation Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/29—Three-dimensional machined; miscellaneous
Definitions
- Seal carrier for a turbo machine with slot-like openings in the seal body
- the present invention relates to a seal carrier for a turbomachine, in particular a gas turbine, comprising a carrier base and at least one sealing body, the at least one sealing body being connected to the carrier base and the at least one sealing body being arranged next to one another in the circumferential direction and in the axial direction, in particular regularly Cavities is formed, wherein the cavities extend from the support base in the radial direction and are delimited by a hollow space wall.
- Directional indications such as “axial” or “axial”, “radial” or “radial” and “circumferential” are to be understood as referring to the machine axis of the turbo machine or gas turbine, unless the context explicitly or implicitly something else results.
- a seal carrier which is formed from several carrier segments with a respective honeycomb-shaped seal body.
- a parting line is provided which extends over the entire axial length of the seal carrier.
- Such a parting line makes it possible to compensate for deformations of the Dichtungsträ gers and the honeycomb-shaped seal body due to temperature gradients during operation of the gas turbine.
- a parting line extending over the entire axial length has the disadvantage that the sealing effect is less good in this area.
- the object on which the invention is based is seen to be that of specifying a seal carrier in which deformations due to temperature gradients are reduced while the sealing effect remains essentially the same.
- seal carrier for a turbomachine, in particular a gas turbine, comprising a carrier base and at least one seal body, the
- At least one sealing body is connected to the support base and the at least one sealing body is formed by several cavities next to one another in the circumferential direction and in the axial direction, in particular regularly arranged cavities, the cavities extending from the support base in the radial direction and through a cavity wall are limited.
- the sealing body has a plurality of Dämpfungsab sections which are designed to locally dampen or interrupt the flow of force in the sealing body, the support base being formed continuously in the area of the Dämpfungsab sections.
- the damping sections can be designed as slot-like openings which are provided in each case with two adjacent cavities that these two adjacent cavities are in fluid connection with one another via the relevant opening.
- the flow of force can be influenced, in particular in the circumferential direction within the sealing body, so that deformations due to thermal gradients can be avoided or reduced.
- the slot-like openings can in any case be designed or dimensioned in such a way that the resulting fluid connection between the hollow spaces has little or no influence on the sealing effect of the seal carrier to be achieved.
- the slot-like opening can be provided in a wall section of the cavity wall which forms a common partition between the two adjacent cavities.
- the slot-like opening can extend radially outward from a radially inner edge of the wall section.
- the slot-like opening can have a slot length in the radial direction that is smaller than the radial height of the wall section, in particular about 70% to 99% of the radial height, or is the same as the radial height.
- Such a slot-like opening can be made, for example, by means of rosive machining (also known as electrical discharge machining (EDM)), for example by means of a suitably dimensioned wire.
- EDM electrical discharge machining
- the slot-like openings can have a width in the range of a few hundredths of a millimeter, so that the slot-like openings have hardly any influence on the sealing effect of the sealing body.
- the openings can be arranged distributed on the sealing body in such a way that a cavity is in fluid connection with only a single adjacent cavity.
- the openings can be distributed on the sealing body in such a way that a cavity is in fluid connection with at least two adjacent cavities.
- the openings can be distributed on the sealing body in such a way that there are several adjacent cavities, between which a continuous wall section is formed, so that these adjacent cavities are not in fluid connection with one another.
- the arrangement or distribution of the slot-like openings in relation to the entire sealing body can therefore take place in particular according to the aspects of the above-mentioned reduction of deformations due to temperature gradients.
- the damping sections can be formed by two parallel and overlapping wall sections of two adjacent cavities.
- a type of opening or slot can also be formed between the overlapping wall sections, so that in this case too the adjacent cavities are in fluid connection with one another.
- the damping sections in such a way that the sealing body has greater elasticity in the area of the damping sections, so that the force flow occurring in the sealing body can be reduced or damped due to the elastic expansion of the damping sections.
- the power flow is not interrupted locally in the area of the damping sections, but is at least partially absorbed by the elastic shear design of the damping sections.
- the support base and the sealing body can be designed as semicircular sealing segments, with two sealing segments forming a circumferential seal.
- the above-described seal carrier and / or a sealing body can also be produced or provided by means of additive manufacturing processes.
- the slot-like openings in the sealing body can also be produced in a simple manner using additive manufacturing processes.
- a gas turbine in particular an aircraft gas turbine, with at least one rotor blade ring can have at least one seal carrier described above, which is arranged around the rotor blade ring.
- FIG. 1 shows in a simplified, schematic representation a basic diagram of an aircraft gas turbine.
- FIG. 2 shows, in a simplified, schematic illustration, a perspective illustration of a seal carrier.
- Fig. 3 shows a simplified, schematic representation of a perspective part representation of a sealing body with cavities and slot-like openings as damping sections.
- FIG. 4 shows, in a simplified, schematic representation, the arrangement of slot-like openings in a sealing body.
- Fig. 5 shows in a simplified, schematic representation the arrangement of Schlitzar term openings in a sealing body.
- Fig. 6 shows in a simplified, schematic representation the arrangement of slot-like openings in a sealing body.
- Fig. 7 shows in a simplified, schematic representation the arrangement of slot-like openings in a sealing body.
- Fig. 8 shows in a simplified, schematic representation in the sub-figures A) and B) the arrangement of slot-like openings in a sealing body, wherein the Hohlhoff me have different shapes.
- Fig. 9 shows a simplified, schematic representation of the arrangement of damping sections by overlapping wall sections in a sealing body. .
- the gas turbine 10 comprises a fan 12 which is surrounded by an indicated jacket 14. In the axial direction AR of the gas turbine 10, the fan 12 is followed by a compressor 16 which is accommodated in an indicated inner housing 18 and can be designed in one or more stages.
- the combustion chamber 20 adjoins the compressor 16. Hot exhaust gas flowing out of the combustion chamber then flows through the adjoining turbine 22, which can be designed in one or more stages.
- the turbine 22 comprises a high-pressure turbine 24 and a low-pressure turbine 26.
- a hollow shaft 28 connects the high-pressure turbine 24 to the compressor 16, in particular a high-pressure compressor 29, so that these are driven or rotated together.
- a further inner shaft 30 in the radial direction RR of the turbine connects the low-pressure turbine 26 to the fan 12 and to a low-pressure compressor 32, so that these are driven or rotated together.
- a thrust nozzle 33 which is only indicated here, adjoins the turbine 22.
- an intermediate turbine housing 34 which is arranged around the shafts 28, 30, is arranged between the high-pressure turbine 24 and the low-pressure turbine 26.
- the intermediate turbine housing 34 In its radially outer region 36, the intermediate turbine housing 34 has hot exhaust gases from the high-pressure turbine 24 flowing through it. The hot exhaust gas then reaches an annular space 38 of the low-pressure turbine 26.
- rotor blade rings 27 are shown by way of example. Guide vane rings 31 that are usually present are shown by way of example only for the compressor 32 for reasons of clarity.
- the seal carrier 50 comprises a carrier base 52 and a seal body 54.
- the seal carrier 50 is shown here as a semicircular example. According to such an embodiment, a sealing arrangement can be created by two such seal carriers 50 which surrounds a rotor blade ring.
- the sealing body 54 is shown by way of example and as a detail in FIG. 3.
- the sealing body 54 comprises a plurality of cavities 56 arranged adjacent to one another in the circumferential direction UR or in the axial direction AR.
- the cavities 56 extend inward from the support base 52 in the radial direction RR.
- the cavities 56 are delimited by a respective circumferential cavity wall 58.
- Each cavity wall 58 is formed by a plurality of wall sections 60.
- the cavity walls 58 are honeycomb-shaped or hexagonal in the example shown.
- some of the wall sections 60 are designed with damping sections 62, here for example in the form of slot-like openings 62.
- the slot-like openings 62 are formed in a respective wall section 60 which forms a common partition between two adjacent cavities 56. Through the slot-like opening 62, the two adjacent cavities 56 are in fluid communication with one another through the opening 62.
- the support base 52 which is arranged radially on the outside in relation to the damping sections 62 or the openings 62, is designed to be continuous.
- the slot-like openings 62 extend radially outward from a radially inner edge 64 of the wall section 60.
- the slot-like opening 62 can have a slot length SL in the radial direction RR which is smaller than the radial height RH of the wall section 60, in particular approximately 70% to 99% of the radial height RH.
- slot lengths LL that are the same size as the radial height RH are also conceivable.
- 4 to 7 show the cavities 56 of the sealing body 54 in schematic, simplified representations. Dotted lines schematically indicate respective slot-like openings 62 which are formed in a relevant wall section 60 between two adjacent cavities 56. In the embodiment of FIG.
- the slot-like openings 62 are arranged such that a cavity 56 is only in fluid connection with a single adjacent cavity 56a.
- the sequence of the arrangement of slot-like openings 62 in order circumferential direction UR forms a kind of zigzag line ZL.
- the slot-like openings 62 are arranged along a plurality of essentially parallel zigzag lines ZL.
- the slot-like openings 62 are also arranged in such a way that a cavity 56 is only in fluid connection with a single adjacent cavity 56a.
- the sequence of the arrangement of slot-like openings 62 in relation to the circumferential direction UR forms an inclined line GL.
- the slot-like openings 62 are arranged along a plurality of essentially parallel lines GL.
- the slot-like openings 62 are arranged in such a way that a cavity 56 is in fluid connection with several, here for example two, adjacent cavities 56a, 56b.
- the slot-like openings 62 are arranged in wall sections 60 of the same cavity 56 that are adjacent to one another.
- the slot-like openings 62 are also arranged in such a way that a cavity 56 is only in fluid connection with a single adjacent cavity 56a.
- the slot-like openings 62 are arranged along a plurality of substantially parallel lines OL.
- FIG. 3 Another embodiment can be seen in FIG. 3.
- a cavity 56 is also connected to a plurality of adjacent cavities 56 (as in FIG. 6).
- the slot-like openings 62 are arranged on opposing wall sections 60 of the cavity 56.
- the sealing body 54 does not necessarily have to have honeycomb-shaped cavities 56. Rather, pentagonal cavities 56 as in FIG. 8A or cavities 56 in the form of a notched directional arrow as in FIG. 8B can be provided. Even with these differently shaped cavities 56, adjacent cavities can be in fluid connection with one another by means of a slot-like opening 62 in a wall section 60.
- other shapes for the cavities or the cavity walls are also conceivable, for example triangular or square or a combination of different shapes.
- the damping sections 62 are formed by overlapping wall sections 60a, 60b of mutually adjacent cavities 56.
- the overlapping wall sections 60a, 60b can bear directly against one another, which improves the sealing effect of the sealing body 54.
- a small or minimal gap can also be formed between the overlapping wall sections 60a, 60b.
- the overlapping wall sections 60a, 60b also serve to interrupt the flow of force.
- overlapping wall sections 60a, 60b can also not be provided parallel to the circumferential direction UR, which is shown by way of example in a lower right area of FIG.
- the support base 52 is designed to be continuous in the area of the damping sections 62.
- the openings 62 can be distributed on the sealing body 54 in such a way that there are several adjacent cavities 56, between which a continuous wall section 60c (FIGS. 3 to 9) is formed so that these adjacent Cavities 56 are not in fluid communication with one another.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102019219090.1A DE102019219090A1 (de) | 2019-12-06 | 2019-12-06 | Dichtungsträger für eine Turbomaschine mit schlitzartigen Öffnungen im Dichtungskörper |
PCT/DE2020/000298 WO2021110191A1 (de) | 2019-12-06 | 2020-12-01 | Dichtungsträger für eine turbomaschine mit schlitzartigen öffnungen im dichtungskörper |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4069947A1 true EP4069947A1 (de) | 2022-10-12 |
Family
ID=74235968
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20845675.6A Pending EP4069947A1 (de) | 2019-12-06 | 2020-12-01 | Dichtungsträger für eine turbomaschine mit schlitzartigen öffnungen im dichtungskörper |
Country Status (4)
Country | Link |
---|---|
US (1) | US20230127895A1 (de) |
EP (1) | EP4069947A1 (de) |
DE (1) | DE102019219090A1 (de) |
WO (1) | WO2021110191A1 (de) |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6610416B2 (en) * | 2001-04-26 | 2003-08-26 | General Electric Company | Material treatment for reduced cutting energy and improved temperature capability of honeycomb seals |
DE10305899B4 (de) * | 2003-02-13 | 2012-06-14 | Alstom Technology Ltd. | Dichtungsanordnung zur Dichtspaltreduzierung bei einer Strömungsrotationsmaschine |
US7105219B2 (en) * | 2004-05-27 | 2006-09-12 | Mitsubishi Heavy Industries, Ltd. | Brazing construction and method of brazing an abradable sealing material |
DE102010062087A1 (de) * | 2010-11-29 | 2012-05-31 | Siemens Aktiengesellschaft | Strömungsmaschine mit Dichtstruktur zwischen drehenden und ortsfesten Teilen sowie Verfahren zur Herstellung dieser Dichtstruktur |
DE102015216208A1 (de) * | 2015-08-25 | 2017-03-02 | Rolls-Royce Deutschland Ltd & Co Kg | Dichtelement für eine Turbomaschine, Turbomaschine mit einem Dichtelement und Verfahren zur Herstellung eines Dichtelementes |
JP6088029B2 (ja) * | 2015-11-19 | 2017-03-01 | 三菱重工業株式会社 | シール装置 |
EP3375980B1 (de) * | 2017-03-13 | 2019-12-11 | MTU Aero Engines GmbH | Dichtungsträger für eine strömungsmaschine |
-
2019
- 2019-12-06 DE DE102019219090.1A patent/DE102019219090A1/de active Pending
-
2020
- 2020-12-01 WO PCT/DE2020/000298 patent/WO2021110191A1/de unknown
- 2020-12-01 US US17/781,219 patent/US20230127895A1/en active Pending
- 2020-12-01 EP EP20845675.6A patent/EP4069947A1/de active Pending
Also Published As
Publication number | Publication date |
---|---|
WO2021110191A1 (de) | 2021-06-10 |
DE102019219090A1 (de) | 2021-06-10 |
US20230127895A1 (en) | 2023-04-27 |
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