EP2796668A3 - Casing section of a turbo engine compressor or turbo engine turbine stage - Google Patents
Casing section of a turbo engine compressor or turbo engine turbine stage Download PDFInfo
- Publication number
- EP2796668A3 EP2796668A3 EP14164186.0A EP14164186A EP2796668A3 EP 2796668 A3 EP2796668 A3 EP 2796668A3 EP 14164186 A EP14164186 A EP 14164186A EP 2796668 A3 EP2796668 A3 EP 2796668A3
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbo engine
- turbine stage
- casing section
- compressor
- turbo
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- 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
- F01D11/125—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 with a reinforcing structure
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/183—Two-dimensional patterned zigzag
-
- 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
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/711—Shape curved convex
-
- 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
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Die Erfindung betrifft einen Gehäuseabschnitt einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe, der einen, insbesondere geschlossenen und kreisringartigen, radial äußeren Mantel aufweist. Der radial äußere Mantel weist radial nach innen erstreckende Stege auf, die gegen den Radius geneigt sind.The invention relates to a housing section of a turbomachinery compressor or turbomachine turbine stage, which has a, in particular closed and annular, radially outer jacket. The radially outer shell has radially inwardly extending webs which are inclined to the radius.
Gasturbine mit einem zugehörigen Gehäuseabschnitt. Gas turbine with an associated housing section.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102013207452.2A DE102013207452A1 (en) | 2013-04-24 | 2013-04-24 | Housing portion of a turbomachinery compressor or turbomachinery turbine stage |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2796668A2 EP2796668A2 (en) | 2014-10-29 |
EP2796668A3 true EP2796668A3 (en) | 2015-01-21 |
EP2796668B1 EP2796668B1 (en) | 2017-03-01 |
Family
ID=50478268
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14164186.0A Not-in-force EP2796668B1 (en) | 2013-04-24 | 2014-04-10 | Casing section of a turbo engine compressor or turbo engine turbine stage |
Country Status (4)
Country | Link |
---|---|
US (1) | US9771830B2 (en) |
EP (1) | EP2796668B1 (en) |
DE (1) | DE102013207452A1 (en) |
ES (1) | ES2620514T3 (en) |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102015202070A1 (en) | 2015-02-05 | 2016-08-25 | MTU Aero Engines AG | Gas turbine component |
FR3040733B1 (en) * | 2015-09-07 | 2018-08-31 | Poly Shape | CARTER FOR ROTATING MACHINES, ESPECIALLY FOR TURBOMACHINES. |
US20170089213A1 (en) | 2015-09-28 | 2017-03-30 | United Technologies Corporation | Duct with additive manufactured seal |
DE102016201581A1 (en) * | 2016-02-02 | 2017-08-03 | MTU Aero Engines AG | Rotor-stator composite for an axial flow machine and aircraft engine |
US10830097B2 (en) * | 2016-02-04 | 2020-11-10 | General Electric Company | Engine casing with internal coolant flow patterns |
US10209009B2 (en) | 2016-06-21 | 2019-02-19 | General Electric Company | Heat exchanger including passageways |
US10802467B2 (en) * | 2017-01-06 | 2020-10-13 | General Electric Company | Methods of defining internal structures for additive manufacturing |
EP3375984A1 (en) * | 2017-03-17 | 2018-09-19 | MTU Aero Engines GmbH | Casing treatment for a flow machine, method for producing a casing treatment and flow machine |
US11260976B2 (en) | 2019-11-15 | 2022-03-01 | General Electric Company | System for reducing thermal stresses in a leading edge of a high speed vehicle |
US11267551B2 (en) | 2019-11-15 | 2022-03-08 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
US11427330B2 (en) | 2019-11-15 | 2022-08-30 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
US11260953B2 (en) | 2019-11-15 | 2022-03-01 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
US11352120B2 (en) | 2019-11-15 | 2022-06-07 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
US11466593B2 (en) | 2020-01-07 | 2022-10-11 | Raytheon Technologies Corporation | Double walled stator housing |
US11745847B2 (en) | 2020-12-08 | 2023-09-05 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
US11407488B2 (en) | 2020-12-14 | 2022-08-09 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
US11577817B2 (en) | 2021-02-11 | 2023-02-14 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2313161A (en) * | 1996-05-14 | 1997-11-19 | Rolls Royce Plc | Turbine casing comprising axially connected rings with integral stator vanes. |
US6182531B1 (en) * | 1998-06-12 | 2001-02-06 | The Boeing Company | Containment ring for flywheel failure |
EP1857655B1 (en) * | 2006-05-16 | 2010-12-29 | Rolls-Royce plc | A liner panel |
EP2305985A2 (en) * | 2009-09-25 | 2011-04-06 | Rolls-Royce plc | Containment casing for an aero engine |
EP2363576A2 (en) * | 2010-03-05 | 2011-09-07 | Rolls-Royce plc | Containment casing for an aircraft engine |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3046648A (en) * | 1959-04-13 | 1962-07-31 | Aircraft Prec Products Inc | Method of manufacturing replaceable labyrinth type seal assembly |
US3365172A (en) * | 1966-11-02 | 1968-01-23 | Gen Electric | Air cooled shroud seal |
US3719365A (en) * | 1971-10-18 | 1973-03-06 | Gen Motors Corp | Seal structure |
USRE30600E (en) * | 1973-02-23 | 1981-05-05 | International Harvester Company | Compliant structural members |
GB2017228B (en) * | 1977-07-14 | 1982-05-06 | Pratt & Witney Aircraft Of Can | Shroud for a turbine rotor |
FR2467978A1 (en) * | 1979-10-23 | 1981-04-30 | Snecma | RETENTION DEVICE FOR A COMPRESSOR CASE OF A TURBOMACHINE |
US4452335A (en) * | 1982-05-03 | 1984-06-05 | United Technologies Corporation | Sound absorbing structure for a gas turbine engine |
US5160248A (en) * | 1991-02-25 | 1992-11-03 | General Electric Company | Fan case liner for a gas turbine engine with improved foreign body impact resistance |
US5520508A (en) * | 1994-12-05 | 1996-05-28 | United Technologies Corporation | Compressor endwall treatment |
US5791871A (en) * | 1996-12-18 | 1998-08-11 | United Technologies Corporation | Turbine engine rotor assembly blade outer air seal |
GB0116988D0 (en) * | 2000-08-11 | 2001-09-05 | Rolls Royce Plc | A gas turbine engine blade containment assembly |
GB0510538D0 (en) * | 2005-05-24 | 2005-06-29 | Rolls Royce Plc | A rotor blade containment assembly for a gas turbine engine |
US8371009B2 (en) * | 2007-12-12 | 2013-02-12 | General Electric Company | Methods for repairing composite containment casings |
FR2925118B1 (en) * | 2007-12-14 | 2009-12-25 | Snecma | ABRADABLE SUPPORT PANEL IN A TURBOMACHINE |
GB0813820D0 (en) * | 2008-07-29 | 2008-09-03 | Rolls Royce Plc | A fan casing for a gas turbine engine |
US8202041B2 (en) * | 2008-10-31 | 2012-06-19 | Pratt & Whitney Canada Corp | Fan case for turbofan engine |
US8500390B2 (en) * | 2010-05-20 | 2013-08-06 | Pratt & Whitney Canada Corp. | Fan case with rub elements |
GB201020143D0 (en) * | 2010-11-29 | 2011-01-12 | Rolls Royce Plc | A gas turbine engine blade containment arrangement |
GB201103682D0 (en) * | 2011-03-04 | 2011-04-20 | Rolls Royce Plc | A turbomachine casing assembly |
-
2013
- 2013-04-24 DE DE102013207452.2A patent/DE102013207452A1/en not_active Ceased
-
2014
- 2014-04-10 ES ES14164186.0T patent/ES2620514T3/en active Active
- 2014-04-10 EP EP14164186.0A patent/EP2796668B1/en not_active Not-in-force
- 2014-04-22 US US14/258,656 patent/US9771830B2/en not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2313161A (en) * | 1996-05-14 | 1997-11-19 | Rolls Royce Plc | Turbine casing comprising axially connected rings with integral stator vanes. |
US6182531B1 (en) * | 1998-06-12 | 2001-02-06 | The Boeing Company | Containment ring for flywheel failure |
EP1857655B1 (en) * | 2006-05-16 | 2010-12-29 | Rolls-Royce plc | A liner panel |
EP2305985A2 (en) * | 2009-09-25 | 2011-04-06 | Rolls-Royce plc | Containment casing for an aero engine |
EP2363576A2 (en) * | 2010-03-05 | 2011-09-07 | Rolls-Royce plc | Containment casing for an aircraft engine |
Also Published As
Publication number | Publication date |
---|---|
US9771830B2 (en) | 2017-09-26 |
EP2796668A2 (en) | 2014-10-29 |
EP2796668B1 (en) | 2017-03-01 |
DE102013207452A1 (en) | 2014-11-13 |
US20140321998A1 (en) | 2014-10-30 |
ES2620514T3 (en) | 2017-06-28 |
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