EP2687684A1 - Revêtement abradable avec rainures spiralées dans une turbomachine - Google Patents

Revêtement abradable avec rainures spiralées dans une turbomachine Download PDF

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Publication number
EP2687684A1
EP2687684A1 EP12176790.9A EP12176790A EP2687684A1 EP 2687684 A1 EP2687684 A1 EP 2687684A1 EP 12176790 A EP12176790 A EP 12176790A EP 2687684 A1 EP2687684 A1 EP 2687684A1
Authority
EP
European Patent Office
Prior art keywords
groove
turbomachine according
turbomachine
blade
grooves
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.)
Withdrawn
Application number
EP12176790.9A
Other languages
German (de)
English (en)
Inventor
Giovanni Brignole
André Werner
Tobias Mayenberger
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 AG
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 AG filed Critical MTU Aero Engines AG
Priority to EP12176790.9A priority Critical patent/EP2687684A1/fr
Publication of EP2687684A1 publication Critical patent/EP2687684A1/fr
Withdrawn legal-status Critical Current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
    • 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

Definitions

  • the present invention relates to a turbomachine, such as a stationary gas turbine or an aircraft engine, with a housing and moving in the housing about a rotational axis moving blades, the blade tips at least partially rubbing during operation arranged on the housing Anstreifbelag. Moreover, the present invention relates to a method for producing such a turbomachine.
  • a turbomachine such as a stationary gas turbine or an aircraft engine
  • turbomachines such as aircraft engines, in which rotor blades of a rotor rotate about a rotation axis within a housing surrounding a flow passage, it is necessary for high efficiency that no gap occurs between the blades and the surrounding housing, resulting in efficiency losses could lead.
  • a corresponding turbomachine is already exposed to different temperatures due to the different loads during operation, which cause the distance between housing and blade tips varies, it is known in such flow machines in the field of blades, for example, the compressor of an aircraft engine so-called inlet or To provide squish coatings that can be touched by the blade tips.
  • the run-in or abradable coatings are made relatively soft and the tips of the blades are preferably provided with a blade tip armor, so that the blade tips can grind into the inlet or squint and the material removal takes place substantially in the region of the squealer and not on the blade tips ,
  • the abradable coating in the region of the rotor blades is provided circumferentially on the housing wall and made smooth, so that along the entire axial blade length, the material of the inlet lining is removed.
  • the invention proposes to design an abradable coating for a turbo-engine in such a way that at least one groove is provided therein, the longitudinal extent of which extends circumferentially around the axis of rotation of the rotor blades of the turbomachine with an additional axial component.
  • a corresponding groove can thus be arranged helically around the axis of rotation or be formed by a circular groove arranged at an angle to the axis of rotation.
  • the abradable coating can be arranged in one piece circumferentially or segmentally circumferentially about the axis of rotation of the turbomachine on the housing of the turbomachine, wherein the housing has a wide variety of components and layers, such as inner and outer housings. It is only essential here that the abradable coating can come into contact with the blade tips of the rotor blades, at least under certain operating conditions.
  • the contact area of the blade tips can be reduced with the squeal layer in a simple manner
  • a uniform material removal over the entire axial blade length is given and the seal between the blade and the squish or housing for the axially flowing fluid is maintained.
  • a plurality of grooves parallel to each other and / or axially and / or tangentially or along the circumference can be arranged offset from one another.
  • the helical shapes can also be arranged inside each other, so that multi-start screw shapes can be realized.
  • the pitch of the spiral or Helixnut or the inclination of an inclined axis of rotation of the blades annular groove can be selected depending on the number and / or length of the grooves and the axial chord length of the corresponding blade in a suitable manner, in particular so that at Turning the blades results in a total uniform material removal at the blade tip.
  • the number of grooves may be between ten and fifty, preferably fifteen and thirty.
  • the grooves may extend along the axis of rotation along a fraction or a multiple of a revolution, so that in the axial direction of the turbomachine very short, fragmentary screw shapes can be provided up to very long helical shapes.
  • the axial groove width and the groove depth in the radial direction may be formed relative to the axial length of the blade tip, which is also referred to as the axial chord length.
  • the grooves may have correspondingly larger groove widths and larger groove depths, whereas for smaller blades having smaller axial chord lengths the groove width and / or groove depth may be smaller.
  • the axial groove width may be 1% to 20% of the axial chord length or 2% to 15% of the axial chord length.
  • the groove depth can be selected in a range of 0.5% to 10% of the axial chord length, in particular 1% to 5% of the axial chord length.
  • the Anstreifbelag may additionally have other profiles, such as radially encircling grooves, so only ring or circular along a circumferential radius and thus have no component of their longitudinal extent in the axial direction of the turbomachine, but a constant have axial position.
  • Such radially encircling grooves can in particular limit regions with helically encircling grooves.
  • the groove depth and / or groove width can vary along the groove, wherein in particular the groove depth at the ends of the groove can continuously decrease to zero.
  • the blade tips of respective turbomachines may have blade tip armor.
  • the squint coating can be sprayed onto corresponding components of the housing, in particular by thermal spraying applied.
  • Such materials can be machined by machining processes to create the grooves.
  • the Fig. 1 shows a perspective view of a Anstreifbelag 1, as it may be provided for limiting a flow channel in a turbomachine, such as an aircraft engine or a stationary gas turbine.
  • a turbomachine such as an aircraft engine or a stationary gas turbine.
  • the Anstreifbelag 1 is shown in an annular shape, ie circumferentially about an axis of rotation, not shown, about which rotate the blades of the turbomachine.
  • the Anstreifbelag 1 may also be provided segment-shaped, for example, divided into several housing segments.
  • a plurality of helical grooves 2, 2 ' are arranged in the abradable coating 1, which are guided in parallel helically along the abradable coating.
  • the grooves 2, 2 ' may be made entirely circumferentially with one or more revolutions about the axis of rotation of the blades or as parts of a revolution which are guided only along part of the circumference of the abradable pad 1 or a surrounding housing.
  • the grooves 2, 2 ' are arranged offset both along the circumference and in the axial direction to each other and form a kind of thread on the inside of the annular abradable coating.
  • the Fig. 2 shows a detail of the abradable coating with the groove 2 and arranged between the groove portions of the groove 2 web portions 3 of the abradable coating.
  • the Fig. 3 shows in the sub-images a) and b) the situation when a blade 4 with the blade tip strikes the Anstreifbelag.
  • the blade tip 5 which may have an armor, touches the Anstreifbelag 1, in which the grooves 2 are arranged circumferentially helically.
  • the regions of the blade tip 5 which are marked with the arrows 6 and shown thicker, direct material contact between the blade 4 and the squish coating 1 occurs, so that a material take-off takes place here when the blade rotates.
  • no direct material contact between the blade 4 or the blade tip 5 and the squib covering 1 is given.
  • the running resistance is reduced by the lower contact surface between the blade 4 and the squish coating 1, while at the same time in the axial direction, a seal between the blade 4 and squealer 1 and the housing is given, so that flow losses through a gap between the blade 4 and housing or squish is avoided.
  • the angle of rotation between the situation in Fig. 3a) and 3b ) is in the embodiment shown 10 °.
  • the heights of the helical arrangement of the grooves can also be chosen with other suitable values.
  • the region in which grooves are provided can also be closed by circumferential grooves 7, which are not helically provided, but circularly circulating in an axially constant position, wherein the groove is formed perpendicular to the axis of rotation. This is in Fig. 4 shown.
  • the shows Fig. 5 in that the grooves 2 do not have to have a constant groove depth, but that in particular at the ends 8 of the grooves, the grooves can be formed by a continuously decreasing groove depth.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP12176790.9A 2012-07-17 2012-07-17 Revêtement abradable avec rainures spiralées dans une turbomachine Withdrawn EP2687684A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12176790.9A EP2687684A1 (fr) 2012-07-17 2012-07-17 Revêtement abradable avec rainures spiralées dans une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12176790.9A EP2687684A1 (fr) 2012-07-17 2012-07-17 Revêtement abradable avec rainures spiralées dans une turbomachine

Publications (1)

Publication Number Publication Date
EP2687684A1 true EP2687684A1 (fr) 2014-01-22

Family

ID=46578865

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12176790.9A Withdrawn EP2687684A1 (fr) 2012-07-17 2012-07-17 Revêtement abradable avec rainures spiralées dans une turbomachine

Country Status (1)

Country Link
EP (1) EP2687684A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3091193A1 (fr) * 2015-05-08 2016-11-09 United Technologies Corporation Matériau abradable et système associé
EP3181828A1 (fr) * 2015-12-17 2017-06-21 United Technologies Corporation Joint d'air extérieur d'aube doté de bouclier d'air intégré
US10954810B2 (en) * 2018-12-17 2021-03-23 Raytheon Technologies Corporation Additive manufactured integrated rub-strip for attritable engine applications

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB839325A (en) * 1955-08-18 1960-06-29 Fur Stromungsmaschinen Ges M B Improvements in and relating to stator casings for gas turbines
GB2017228A (en) * 1977-07-14 1979-10-03 Pratt & Witney Aircraft Of Can Shroud for a turbine rotor
US6203021B1 (en) * 1996-12-10 2001-03-20 Chromalloy Gas Turbine Corporation Abradable seal having a cut pattern
EP1111195A1 (fr) 1999-12-20 2001-06-27 Sulzer Metco AG Surface structurée utilisée comme couche de rasage dans les turbomachines
WO2002033292A1 (fr) * 2000-10-20 2002-04-25 Wilhelm Prinz Étranglement de protection pour cavité de joint
EP1553304A2 (fr) * 2004-01-08 2005-07-13 Samsung Electronics Co., Ltd. Turbo-compresseur
EP1801361A1 (fr) * 2005-12-22 2007-06-27 Rolls-Royce plc Boîtier de ventilateur ou de compresseur
EP1876326A2 (fr) * 2006-07-05 2008-01-09 United Technologies Corporation Rotor pour moteur de turbine à gaz
EP2050931A2 (fr) * 2007-10-16 2009-04-22 United Technologies Corporation Systèmes et procédés impliquant des joints abradables étanches à l'air
DE102007053135A1 (de) * 2007-11-08 2009-05-14 Mtu Aero Engines Gmbh Gasturbinenbauteil, insbesondere Flugtriebwerksbauteil bzw. Verdichterbauteil

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB839325A (en) * 1955-08-18 1960-06-29 Fur Stromungsmaschinen Ges M B Improvements in and relating to stator casings for gas turbines
GB2017228A (en) * 1977-07-14 1979-10-03 Pratt & Witney Aircraft Of Can Shroud for a turbine rotor
US6203021B1 (en) * 1996-12-10 2001-03-20 Chromalloy Gas Turbine Corporation Abradable seal having a cut pattern
EP1111195A1 (fr) 1999-12-20 2001-06-27 Sulzer Metco AG Surface structurée utilisée comme couche de rasage dans les turbomachines
WO2002033292A1 (fr) * 2000-10-20 2002-04-25 Wilhelm Prinz Étranglement de protection pour cavité de joint
EP1553304A2 (fr) * 2004-01-08 2005-07-13 Samsung Electronics Co., Ltd. Turbo-compresseur
EP1801361A1 (fr) * 2005-12-22 2007-06-27 Rolls-Royce plc Boîtier de ventilateur ou de compresseur
EP1876326A2 (fr) * 2006-07-05 2008-01-09 United Technologies Corporation Rotor pour moteur de turbine à gaz
EP2050931A2 (fr) * 2007-10-16 2009-04-22 United Technologies Corporation Systèmes et procédés impliquant des joints abradables étanches à l'air
DE102007053135A1 (de) * 2007-11-08 2009-05-14 Mtu Aero Engines Gmbh Gasturbinenbauteil, insbesondere Flugtriebwerksbauteil bzw. Verdichterbauteil

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3091193A1 (fr) * 2015-05-08 2016-11-09 United Technologies Corporation Matériau abradable et système associé
US9951642B2 (en) 2015-05-08 2018-04-24 United Technologies Corporation Intermittent grooved soft abradable material to reduce blade tip temperature
EP4209659A1 (fr) * 2015-05-08 2023-07-12 Raytheon Technologies Corporation Matériau abradable à rainures intermittentes pour réduire la température de pointe d'aube
EP3181828A1 (fr) * 2015-12-17 2017-06-21 United Technologies Corporation Joint d'air extérieur d'aube doté de bouclier d'air intégré
US10443426B2 (en) 2015-12-17 2019-10-15 United Technologies Corporation Blade outer air seal with integrated air shield
US10954810B2 (en) * 2018-12-17 2021-03-23 Raytheon Technologies Corporation Additive manufactured integrated rub-strip for attritable engine applications

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