EP1721064A1 - Ring structure with a metal design having a run-in lining - Google Patents
Ring structure with a metal design having a run-in liningInfo
- Publication number
- EP1721064A1 EP1721064A1 EP05715035A EP05715035A EP1721064A1 EP 1721064 A1 EP1721064 A1 EP 1721064A1 EP 05715035 A EP05715035 A EP 05715035A EP 05715035 A EP05715035 A EP 05715035A EP 1721064 A1 EP1721064 A1 EP 1721064A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- metal
- ring structure
- hollow chamber
- structure according
- 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.)
- Granted
Links
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
- F01D11/122—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 erodable or abradable material
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/236—Diffusion bonding
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/238—Soldering
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/601—Fabrics
Definitions
- the invention relates to a ring structure in metal construction according to the preamble of patent claim 1.
- the wall structure should initially be sufficiently dimensionally stable and geometrically accurate. Thermal and mechanical influences should change the geometry as little as possible. The mostly hot working gas should essentially only be applied to the inside of the structure; leakage losses through the structure should be minimized. In stationary operation, it is advantageous if the change in dimension of the wall structure, which is particularly thermally induced, is matched in time and size to that of the bladed rotor. Since mechanical contacts between the blade tips and the wall structure can hardly be avoided under special loads, the inside of the wall structure should at least be designed to be deformable or flexible or shrinkable on the blade tip side.
- DE 100 20 673 C2 discloses a ring structure in metal construction for the rotor blade area of axially flowed through compressor and turbine stages.
- the ring structure disclosed there has an annular outer wall which is designed as a closed, mechanically stable housing wall of the compressor or turbine stage.
- the ring structure disclosed therein comprises an inner wall in the form of a ring and a connecting structure in the form of a hollow chamber structure, the connecting structure in the form of a hollow chamber structure being sandwiched between the outer wall and the inner wall.
- the connecting structure designed as a hollow chamber structure is connected on the one hand to the outer wall and on the other hand to the inner wall.
- the annular space structure according to DE 100 20 673 C2 has an inner wall, the circumference of which is interrupted several times by axial or predominantly axial expansion joints.
- An inner wall segmented in this way by expansion joints has the disadvantage that flow losses can occur.
- an inner wall segmented in this way increases the complexity of the ring structure and thus the assembly and production effort.
- flaking, washing out or erosion damage can occur on the edges of the expansion joints during operation, which increases the flow losses again. Proceeding from this, the present invention is based on the problem of creating a novel ring structure in metal construction.
- the inner wall is designed as a closed, mechanically stable structure which serves as an inlet covering for the blade tips and is made of a metal mesh and / or a metal felt.
- the metal mesh and / or the metal felt is preferably formed from a metal alloy which is resistant to oxidation at high temperatures, in particular from an alloy based on iron, nickel or cobalt.
- a ring structure in metal manner is proposed, the inner wall of which is closed and is formed from a metal mesh and / or a metal felt. Flow losses can be minimized due to the closed structure of the inner wall. Furthermore, compared to the segmented design known from the prior art, there is a simpler design for the ring structure according to the invention.
- a high mechanical stability can be achieved on the one hand by using a metal mesh or a metal felt for the closed inner wall, on the other hand circumferential expansions do not lead to the formation of cracks in the inner wall.
- the metal mesh or metal felt can absorb thermally generated strains without cracking.
- Figure 1 shows a ring structure according to the invention in metal construction according to a first embodiment of the invention in a schematic side view.
- FIG. 4 shows detail IV of the ring structure according to FIG. 3;
- 5 shows a ring structure according to the invention in metal construction according to a third exemplary embodiment of the invention in a schematic side view; and 6 shows the detail VI of the ring structure according to FIG. 5.
- FIG. 1 and 2 show a first exemplary embodiment of a ring structure 10 according to the invention, FIG. 2 showing detail II of FIG. 1 on an enlarged scale.
- the first and 2 comprises a circular outer wall 11, a circular inner wall 12 and a connecting structure 13 sandwiched between the outer wall 11 and the inner wall 12.
- the outer wall 11 is a closed, mechanically stable housing wall of a compressor stage or Turbine stage of a gas turbine, in particular an aircraft engine.
- the connecting structure 13 positioned between the outer wall 11 and the inner wall 12 is designed as a hollow chamber structure.
- the hollow chamber structure 13 can have hexagonal, rectangular or round chambers in cross-section parallel to the inner wall or outer wall of the ring structure 10. In the case of chambers with a hexagonal cross section, one speaks of a so-called honeycomb structure.
- the inner wall 12 is designed as a closed and mechanically stable structure.
- the inner wall 12 serves on the one hand for the mechanical stabilization of the ring structure 10 and on the other hand as an inlet lining for rotating blade tips (not shown) of rotating blades.
- the inner wall 12, which is designed as a self-contained structure in the sense of the present invention, is formed from a metal mesh and / or a metal felt.
- a metal mesh is a structure in which metallic fibers or threads run in a systematically structured manner.
- a metal felt on the other hand, is a structure in which metallic fibers are randomly or stochastically distributed.
- the term metal mesh should also be understood to mean a knitted fabric made of metal fibers.
- the inner wall 12 By using a self-contained structure made of metal mesh and / or metal felt as the inner wall 12, gaps or joints within the inner wall 12 are avoided. Flow losses can thereby be minimized.
- the metal mesh or metal felt can absorb thermally generated expansions without the risk of cracking. This makes it possible to dispense with expansion joints within the inner wall 12.
- the inner wall 12, which is designed as a closed structure, has a simple construction.
- connection structure 13 is firmly connected on the one hand at the radially outer end to the outer wall 11 and on the other hand at the radially inner end to the inner wall 12.
- the connection structure 13 can thus be soldered to the inner wall 12 and the outer wall 11.
- the outer wall 11, the inner wall 12 and the connecting structure 13 are accordingly firmly connected to one another to form an overall structure, namely to the ring structure 10 according to the invention.
- the inner wall 12 serves on the one hand for the mechanical stabilization of the ring structure 10 according to the invention and on the other hand as an inlet covering.
- the inner wall 12 or the metal mesh and / or the metal felt of the inner wall 12 is made of a material which is resistant to oxidation at high temperatures.
- the metal mesh or the metal felt can be made of a metal alloy based on a nickel material, iron material or also cobalt material.
- the metal fabric or the metal felt is connected to one another to form the annular inner wall 12 to form at least one butt joint.
- 1 and 2 show a butt joint 14 of two mutually touching edges of the metal mesh or metal felt to provide the inner wall 12.
- the edges of the butt joint 14 run in the radial direction, so that the two edges are in the region of the Touch butt joint 14, but there is no overlap.
- FIGS. 3 to 6 show two further exemplary embodiments of ring structures 15 and 16 according to the invention.
- the exemplary embodiments in FIGS. 3 to 6 differ from the exemplary embodiment in FIGS. 1 and 2 only in the design of the butt joint in the area of the inner wall 12.
- the other details are correct the exemplary embodiments correspond, so that the same reference numbers are used to avoid unnecessary repetitions for the same assemblies.
- a joint 17 is shown which extends obliquely to the radial direction, that is to say extends on the one hand in the radial direction and on the other hand in the circumferential direction of the ring structure 15. With a butt joint 17 designed in this way, the corresponding edges overlap without thickening of material.
- 5 and 6 show an exemplary embodiment of a ring structure 16 according to the invention, in which there is an abutment 18 in the region of the inner wall 12, in which abutting edges overlap one another to form a material thickening 19.
- the material thickening 19 is directed radially outward, the material thickening 19 accordingly extends into the area of the connecting structure 13.
- the chambers of the connecting structure 13 can be shortened accordingly in the area in which the material thickening 19 runs.
- a metallic ring structure in which the inner wall is closed and is further made from a metal mesh and / or a metal felt. Flow losses can be minimized due to the closed structure of the inner wall.
- thermal expansions can be absorbed without cracks. This enables a significantly simpler construction of a ring structure.
- the inner wall made of the metal felt or metal mesh continues to serve as a running-in covering.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004010236A DE102004010236A1 (en) | 2004-03-03 | 2004-03-03 | Metal ring structure for sealing gap between rotor blade tips and stator in e.g. gas turbine, has inner wall formed by metal fabric or felt |
PCT/DE2005/000333 WO2005085600A1 (en) | 2004-03-03 | 2005-02-28 | Ring structure with a metal design having a run-in lining |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1721064A1 true EP1721064A1 (en) | 2006-11-15 |
EP1721064B1 EP1721064B1 (en) | 2010-06-02 |
Family
ID=34853918
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05715035A Expired - Fee Related EP1721064B1 (en) | 2004-03-03 | 2005-02-28 | Ring structure with a metal design having a run-in lining |
Country Status (4)
Country | Link |
---|---|
US (1) | US8061965B2 (en) |
EP (1) | EP1721064B1 (en) |
DE (2) | DE102004010236A1 (en) |
WO (1) | WO2005085600A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2495399B1 (en) | 2011-03-03 | 2016-11-23 | Safran Aero Booster S.A. | Segmented shroud assembly suitable for compensating a rotor misalignment relative to the stator |
ES2705532T3 (en) | 2012-10-30 | 2019-03-25 | MTU Aero Engines AG | Turbine and turbomachine ring |
US10472980B2 (en) * | 2017-02-14 | 2019-11-12 | General Electric Company | Gas turbine seals |
TR201705399A2 (en) * | 2017-04-11 | 2017-09-21 | Sdm Siradisi Arge Ve Muehendislik Sanayi Ticaret Anonim Sirketi | Knit fabric reinforced leaf felt |
DE102017211316A1 (en) | 2017-07-04 | 2019-01-10 | MTU Aero Engines AG | Turbomachinery sealing ring |
Family Cites Families (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3126149A (en) * | 1964-03-24 | Foamed aluminum honeycomb motor | ||
US3042365A (en) * | 1957-11-08 | 1962-07-03 | Gen Motors Corp | Blade shrouding |
US3068016A (en) * | 1958-03-31 | 1962-12-11 | Gen Motors Corp | High temperature seal |
US3056583A (en) * | 1960-11-10 | 1962-10-02 | Gen Electric | Retaining means for turbine shrouds and nozzle diaphragms of turbine engines |
US3053694A (en) * | 1961-02-20 | 1962-09-11 | Gen Electric | Abradable material |
US3146992A (en) * | 1962-12-10 | 1964-09-01 | Gen Electric | Turbine shroud support structure |
US3425665A (en) * | 1966-02-24 | 1969-02-04 | Curtiss Wright Corp | Gas turbine rotor blade shroud |
US3365172A (en) * | 1966-11-02 | 1968-01-23 | Gen Electric | Air cooled shroud seal |
US3423070A (en) * | 1966-11-23 | 1969-01-21 | Gen Electric | Sealing means for turbomachinery |
BE756582A (en) * | 1969-10-02 | 1971-03-01 | Gen Electric | CIRCULAR SCREEN AND SCREEN HOLDER WITH TEMPERATURE ADJUSTMENT FOR TURBOMACHINE |
US3867061A (en) | 1973-12-26 | 1975-02-18 | Curtiss Wright Corp | Shroud structure for turbine rotor blades and the like |
US4135851A (en) * | 1977-05-27 | 1979-01-23 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Composite seal for turbomachinery |
US4409054A (en) * | 1981-01-14 | 1983-10-11 | United Technologies Corporation | Method for applying abradable material to a honeycomb structure and the product thereof |
GB2095749B (en) * | 1981-03-25 | 1984-12-12 | Rolls Royce | Gas turbine engine having improved resistance for foreign object ingestion damage |
GB2117843B (en) * | 1982-04-01 | 1985-11-06 | Rolls Royce | Compressor shrouds |
US4867639A (en) * | 1987-09-22 | 1989-09-19 | Allied-Signal Inc. | Abradable shroud coating |
IE67360B1 (en) * | 1990-09-25 | 1996-03-20 | United Technologies Corp | Apparatus and method for a stator assembly of a rotary machine |
US5228195A (en) * | 1990-09-25 | 1993-07-20 | United Technologies Corporation | Apparatus and method for a stator assembly of a rotary machine |
US5304031A (en) * | 1993-02-25 | 1994-04-19 | The United States Of America As Represented By The Secretary Of The Air Force | Outer air seal for a gas turbine engine |
US5738490A (en) * | 1996-05-20 | 1998-04-14 | Pratt & Whitney Canada, Inc. | Gas turbine engine shroud seals |
DE19828065A1 (en) | 1998-06-24 | 1999-12-30 | Bmw Rolls Royce Gmbh | Honeycomb structure seal especially for a gas turbine |
US6120242A (en) * | 1998-11-13 | 2000-09-19 | General Electric Company | Blade containing turbine shroud |
DE19937577A1 (en) * | 1999-08-09 | 2001-02-15 | Abb Alstom Power Ch Ag | Frictional gas turbine component |
DE10020673C2 (en) * | 2000-04-27 | 2002-06-27 | Mtu Aero Engines Gmbh | Ring structure in metal construction |
US6619913B2 (en) * | 2002-02-15 | 2003-09-16 | General Electric Company | Fan casing acoustic treatment |
GB0218060D0 (en) * | 2002-08-03 | 2002-09-11 | Alstom Switzerland Ltd | Sealing arrangements |
JP4285134B2 (en) * | 2003-07-04 | 2009-06-24 | 株式会社Ihi | Shroud segment |
-
2004
- 2004-03-03 DE DE102004010236A patent/DE102004010236A1/en not_active Ceased
-
2005
- 2005-02-28 WO PCT/DE2005/000333 patent/WO2005085600A1/en active Application Filing
- 2005-02-28 US US11/578,862 patent/US8061965B2/en not_active Expired - Fee Related
- 2005-02-28 DE DE502005009677T patent/DE502005009677D1/en active Active
- 2005-02-28 EP EP05715035A patent/EP1721064B1/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2005085600A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2005085600A1 (en) | 2005-09-15 |
EP1721064B1 (en) | 2010-06-02 |
US8061965B2 (en) | 2011-11-22 |
US20090263239A1 (en) | 2009-10-22 |
DE502005009677D1 (en) | 2010-07-15 |
DE102004010236A1 (en) | 2005-09-15 |
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