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US20100202872A1 - Multilayer shielding ring for a flight driving mechanism - Google Patents

Multilayer shielding ring for a flight driving mechanism Download PDF

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Publication number
US20100202872A1
US20100202872A1 US12/733,382 US73338208A US2010202872A1 US 20100202872 A1 US20100202872 A1 US 20100202872A1 US 73338208 A US73338208 A US 73338208A US 2010202872 A1 US2010202872 A1 US 2010202872A1
Authority
US
United States
Prior art keywords
shielding
turbine
layers
embodied
exhaust gas
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.)
Abandoned
Application number
US12/733,382
Other languages
English (en)
Inventor
Wilfried Weidmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WEIDMANN, WILFRIED
Publication of US20100202872A1 publication Critical patent/US20100202872A1/en
Abandoned legal-status Critical Current

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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
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within

Definitions

  • the invention relates to a shielding of a turbine housing or casing of an aircraft engine against the radial escape of blade fragments according to the preamble of the patent claim 1 .
  • the so-called containment protection i.e. the shielding of the housing or casing against possible radially outwardly ejected blade parts or blade fragments
  • the so-called containment protection i.e. the shielding of the housing or casing against possible radially outwardly ejected blade parts or blade fragments
  • LPT low-pressure turbine
  • TEC turbine exhaust gas housing or casing
  • This examination generally determines that the wall thickness of the connection LPT/TEC is sufficiently strongly dimensioned also as a containment protection.
  • FIG. 2 Such a shielding from the prior art is shown in a cutaway portion view in FIG. 2 .
  • the low-pressure turbine 1 is shown with turbine blades 2 , which are arranged within a turbine housing or casing 3 .
  • the turbine blades are arranged axially after a compressor that is not shown and a combustion chamber that is not shown, and are located on a turbine disk that rotates about the engine axis.
  • the turbine housing 3 is connected via a flange 5 with the turbine exhaust gas channel 10 .
  • the turbine exhaust gas channel 10 of the prior art is embodied as a cast part, which also comprises a containment function due to the existing material thickness.
  • the turbine exhaust gas channel with containment function serves to prevent the escape of the blade parts out of the engine housing and thereby to avoid possible damages of the aircraft airframe.
  • the impact area that is determinative for the design is identified by the straight lines enclosing an angle ⁇ .
  • the containment protection is, however, a particular design criterium, because the regular cast part thickness of the turbine exhaust gas channel is no longer sufficient to prevent a possible through-penetration of loose blade parts due to the higher momentum of the blade parts. Therefore, according to the present state, no material-, cost- and weight-optimized low-pressure turbine/turbine exhaust gas channel (LPT/TEC) connection is possible. Rather, the material selection and material thickness of the LPT/TEC connection is determined by the required containment thickness and not by the optimized LPT/TEC connection. The material selection is also determined by the higher requirements for the cast material in the containment area and is thereby made more expensive.
  • LPT/TEC low-pressure turbine/turbine exhaust gas channel
  • the inventive shielding of a turbine housing of an aircraft engine against radial escape of blade fragments, especially for a high-speed low-pressure turbine is characterized in that the shielding is embodied as a rigid ring-shaped component of several layers. Thereby the ring-shaped shielding can be arranged radially within or outside of the turbine housing. In connection with mounting on the turbine housing, the shielding can also direct cooling air, for example from the fan stream flow, in a targeted manner onto the outer skin of the housing. It is further possible that the ring-shaped shielding consists of several segments, whereby production and assembly are simplified. Due to the stiff embodiment, the shielding is protected against external influences, and can be embodied in a self-supporting manner.
  • An advantageous embodiment of the inventive shielding provides that the shielding is arranged on the turbine exhaust gas channel.
  • the shielding is arranged on the turbine exhaust gas channel.
  • an advantageous embodiment of the inventive shielding provides that the shielding is embodied as a forged component.
  • This makes possible a multilayer construction with selection of suitable material layers.
  • the strength is a defining factor, as well as the temperatures present in the area of the low-pressure turbine on the housing or on the LPT/TEC connection.
  • the possibility of the temperature expansion is to be taken into account for a shielding ring having multiple parts in the circumferential direction.
  • a further advantageous embodiment of the inventive shielding provides that the shielding is arranged within the turbine housing. On the one hand this avoids interfering additional structural components outside of the turbine housing, and on the other hand it is hereby prevented that the housing or the LPT/TEC connection is penetrated through in the case of a blade damage, whereby the costs of an engine failure rise further.
  • the shielding is embodied as a flow guide element. This can be the case both for the application of the shielding within or outside of the housing. Thereby additional flow guide elements can be applied on the shielding, or alternatively the shielding itself is formed or mounted in a flow-advantageous manner.
  • the shielding is embodied as a heat shield. This is especially necessary for the installation in the flow channel, i.e. within the turbine housing. However, this can also be suitable for the purpose for installation on the outer circumference of the turbine housing, in order to prevent injuries due to burns on hot engine components during maintenance work.
  • an advantageous embodiment of the inventive shielding provides that the layers are constructed of different materials.
  • highly heat resistant forgeable alloys come into consideration as materials.
  • the strength characteristics, temperature expansion and weight of the shielding can be influenced to the desired extent. This is especially expedient in the sense of a weight- and cost-optimization.
  • an advantageous embodiment of the inventive shielding provides that the layers comprise different thicknesses. Like the material selection, the strength and the weight of the shielding can also be optimized by the selection of the layer thickness, and thereby the costs of the component can be reduced.
  • An advantageous embodiment of the inventive shielding provides that the layers are adapted or tuned to one another in a vibration-optimized manner. Thereby the layers of the multilayer shielding ring are connected in a resonance-free manner in the shielding housing.
  • both the vibration characteristics of the shielding alone, as well as the vibration characteristics of the components coupled with the shielding can be taken into consideration.
  • the variation of the vibration characteristics due to fluid flow thereon and temperature expansion can be taken into consideration in the design and adaptation or tuning of the layers.
  • the shielding comprises an enclosure or mounting frame for different functional layers.
  • enclosure or mounting frame can also encompass a shielding housing with which different layers are connected in a joint-technical manner.
  • the ring-shaped layers can be encased or enclosed or surrounded quasi from three sides, and if applicable can also be received in a floating manner in the mounting frame.
  • FIG. 1 an advantageous embodiment of the present invention, schematically in a cutaway portion
  • FIG. 2 a schematic partial sectional illustration of a shielding of the prior art.
  • FIG. 1 schematically shows in the manner of a cutaway portion, an advantageous embodiment of an inventive shielding 6 on a high-speed low-pressure turbine 1 .
  • the compressor which is not shown in the drawing and the combustion chamber, as well as the high- and medium-pressure turbine which is similarly not shown, are located in the drawing plane on the left hand side, that is to say upstream with regard to the flow.
  • the FIG. 1 shows a cutaway portion of a half-section.
  • FIG. 1 a part of a turbine blade 2 is illustrated, which is arranged within a turbine housing 3 that surrounds the turbine stage in the circumferential direction.
  • the turbine housing 3 is connected with the turbine exhaust gas channel 4 or connected thereto via a material-technically optimized flange connection 5 .
  • the shielding 6 is arranged on the connection of the low-pressure turbine 1 to the turbine exhaust gas channel 4 within the turbine housing 3 .
  • a flange 9 protrudes inwardly in the radial direction on the turbine exhaust gas channel 4 , and the shielding 6 or the shielding housing 7 is flange-connected on the flange 9 .
  • the shielding 6 or the containment ring which is illustrated L-shaped in section and is ring-shaped in the circumferential direction, is embodied as a multilayer forged part in the present example embodiment.
  • the two layers 8 of the shielding 6 are received in a shielding housing 7 and are connected therewith in a forging-technological manner.
  • Both the type of the alloy as well as the layer thickness/number of layers differ from one another in the two layers 8 shown in the example embodiment.
  • the resonance-free shielding 6 in the present example embodiment also comprises integrated heat-shield and flow-guiding function in addition to the containment function.
  • the containment function is presently not integrated in the connection of low-pressure turbine 1 /turbine exhaust gas channel 4 , whereby this connection can be embodied as a weight-optimized cast part.
  • the invention is not limited in its embodiment to the preferred example embodiment set forth above. Rather, a number of variants is conceivable, which also makes use of the solution claimed in the patent claims, also in embodiments of a different type.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/733,382 2007-09-07 2008-08-27 Multilayer shielding ring for a flight driving mechanism Abandoned US20100202872A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102007042767.2 2007-09-07
DE102007042767A DE102007042767A1 (de) 2007-09-07 2007-09-07 Mehrschichtiger Abschirmungsring für einen Flugantrieb
PCT/DE2008/001417 WO2009030197A1 (fr) 2007-09-07 2008-08-27 Anneau de protection multicouche pour système de propulsion d'aéronef

Publications (1)

Publication Number Publication Date
US20100202872A1 true US20100202872A1 (en) 2010-08-12

Family

ID=40221258

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/733,382 Abandoned US20100202872A1 (en) 2007-09-07 2008-08-27 Multilayer shielding ring for a flight driving mechanism

Country Status (5)

Country Link
US (1) US20100202872A1 (fr)
EP (1) EP2191105A1 (fr)
CA (1) CA2698283A1 (fr)
DE (1) DE102007042767A1 (fr)
WO (1) WO2009030197A1 (fr)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014088672A3 (fr) * 2012-09-28 2014-08-14 United Technologies Corporation Écran thermique pour cadre de turbine centrale
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
FR3054527A1 (fr) * 2016-07-29 2018-02-02 Airbus Operations Ensemble pour aeronef comprenant un bouclier de protection contre un eclatement moteur, monte sur le carter d'un module de turbomachine
US9890663B2 (en) 2012-12-31 2018-02-13 United Technologies Corporation Turbine exhaust case multi-piece frame
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10054009B2 (en) 2012-12-31 2018-08-21 United Technologies Corporation Turbine exhaust case multi-piece frame
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10330011B2 (en) 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
US10329957B2 (en) 2012-12-31 2019-06-25 United Technologies Corporation Turbine exhaust case multi-piece framed
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US10487684B2 (en) 2017-03-31 2019-11-26 The Boeing Company Gas turbine engine fan blade containment systems
US10550718B2 (en) 2017-03-31 2020-02-04 The Boeing Company Gas turbine engine fan blade containment systems

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013214389A1 (de) 2013-07-23 2015-01-29 MTU Aero Engines AG Gehäusecontainment
DE102014208883A1 (de) 2014-05-12 2015-12-03 MTU Aero Engines AG Verfahren zum Auslegen einer Turbine

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US2742224A (en) * 1951-03-30 1956-04-17 United Aircraft Corp Compressor casing lining
US3097824A (en) * 1958-11-26 1963-07-16 Bendix Corp Turbine, wheel containment
US3241813A (en) * 1964-01-21 1966-03-22 Garrett Corp Turbine wheel burst containment means
US3849022A (en) * 1973-07-12 1974-11-19 Gen Motors Corp Turbine blade coolant distributor
US4095005A (en) * 1975-08-18 1978-06-13 Nissan Motor Company, Ltd. Method of producing low wear coating reinforced with brazing solder for use as rubbing seal
US4377370A (en) * 1979-10-19 1983-03-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Safety device for a rotating element of a turbine engine
US4547122A (en) * 1983-10-14 1985-10-15 Aeronautical Research Associates Of Princeton, Inc. Method of containing fractured turbine blade fragments
US5267828A (en) * 1992-11-13 1993-12-07 General Electric Company Removable fan shroud panel
US5328324A (en) * 1991-12-14 1994-07-12 Rolls-Royce Plc Aerofoil blade containment
US6059523A (en) * 1998-04-20 2000-05-09 Pratt & Whitney Canada Inc. Containment system for containing blade burst
US6290455B1 (en) * 1999-12-03 2001-09-18 General Electric Company Contoured hardwall containment
US20060233636A1 (en) * 2002-06-05 2006-10-19 Volvo Aero Corporation Turbine and a component
US7163370B2 (en) * 2003-01-23 2007-01-16 Honda Motor Co., Ltd. Gas turbine engine and method of producing the same
US20070031246A1 (en) * 2005-05-24 2007-02-08 Rolls-Royce Plc Containment casing
US20090297331A1 (en) * 2008-04-23 2009-12-03 Snecma Turbomachine casing including a device for preventing instability during contact between the casing and the rotor

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GB1245415A (en) * 1968-09-13 1971-09-08 Rolls Royce Improvements in or relating to fluid flow machines
DE7501892U (de) * 1975-01-23 1976-06-03 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Metall-keramik-heissgasfuehrung mit berstschutz-eigenschaften
DE4223496A1 (de) * 1992-07-17 1994-01-20 Asea Brown Boveri Vorrichtung zum Reduzieren der kinetischen Energie von berstenden Teilen

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2742224A (en) * 1951-03-30 1956-04-17 United Aircraft Corp Compressor casing lining
US3097824A (en) * 1958-11-26 1963-07-16 Bendix Corp Turbine, wheel containment
US3241813A (en) * 1964-01-21 1966-03-22 Garrett Corp Turbine wheel burst containment means
US3849022A (en) * 1973-07-12 1974-11-19 Gen Motors Corp Turbine blade coolant distributor
US4095005A (en) * 1975-08-18 1978-06-13 Nissan Motor Company, Ltd. Method of producing low wear coating reinforced with brazing solder for use as rubbing seal
US4377370A (en) * 1979-10-19 1983-03-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Safety device for a rotating element of a turbine engine
US4547122A (en) * 1983-10-14 1985-10-15 Aeronautical Research Associates Of Princeton, Inc. Method of containing fractured turbine blade fragments
US5328324A (en) * 1991-12-14 1994-07-12 Rolls-Royce Plc Aerofoil blade containment
US5267828A (en) * 1992-11-13 1993-12-07 General Electric Company Removable fan shroud panel
US6059523A (en) * 1998-04-20 2000-05-09 Pratt & Whitney Canada Inc. Containment system for containing blade burst
US6290455B1 (en) * 1999-12-03 2001-09-18 General Electric Company Contoured hardwall containment
US20060233636A1 (en) * 2002-06-05 2006-10-19 Volvo Aero Corporation Turbine and a component
US7163370B2 (en) * 2003-01-23 2007-01-16 Honda Motor Co., Ltd. Gas turbine engine and method of producing the same
US20070031246A1 (en) * 2005-05-24 2007-02-08 Rolls-Royce Plc Containment casing
US20090297331A1 (en) * 2008-04-23 2009-12-03 Snecma Turbomachine casing including a device for preventing instability during contact between the casing and the rotor

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014088672A3 (fr) * 2012-09-28 2014-08-14 United Technologies Corporation Écran thermique pour cadre de turbine centrale
US10167779B2 (en) 2012-09-28 2019-01-01 United Technologies Corporation Mid-turbine frame heat shield
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
US10941674B2 (en) 2012-12-29 2021-03-09 Raytheon Technologies Corporation Multi-piece heat shield
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US10329957B2 (en) 2012-12-31 2019-06-25 United Technologies Corporation Turbine exhaust case multi-piece framed
US10054009B2 (en) 2012-12-31 2018-08-21 United Technologies Corporation Turbine exhaust case multi-piece frame
US9890663B2 (en) 2012-12-31 2018-02-13 United Technologies Corporation Turbine exhaust case multi-piece frame
US10330011B2 (en) 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
FR3054527A1 (fr) * 2016-07-29 2018-02-02 Airbus Operations Ensemble pour aeronef comprenant un bouclier de protection contre un eclatement moteur, monte sur le carter d'un module de turbomachine
US10487684B2 (en) 2017-03-31 2019-11-26 The Boeing Company Gas turbine engine fan blade containment systems
US10550718B2 (en) 2017-03-31 2020-02-04 The Boeing Company Gas turbine engine fan blade containment systems

Also Published As

Publication number Publication date
DE102007042767A1 (de) 2009-03-12
EP2191105A1 (fr) 2010-06-02
CA2698283A1 (fr) 2009-03-12
WO2009030197A1 (fr) 2009-03-12

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Legal Events

Date Code Title Description
AS Assignment

Owner name: MTU AERO ENGINES GMBH, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:WEIDMANN, WILFRIED;REEL/FRAME:024014/0271

Effective date: 20100205

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION