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Patentes

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Número de publicaciónUS20080061515 A1
Tipo de publicaciónSolicitud
Número de solicitudUS 11/530,226
Fecha de publicación13 Mar 2008
Fecha de presentación8 Sep 2006
Fecha de prioridad8 Sep 2006
También publicado comoCA2598329A1, CA2598329C, US8172514, US20090208326
Número de publicación11530226, 530226, US 2008/0061515 A1, US 2008/061515 A1, US 20080061515 A1, US 20080061515A1, US 2008061515 A1, US 2008061515A1, US-A1-20080061515, US-A1-2008061515, US2008/0061515A1, US2008/061515A1, US20080061515 A1, US20080061515A1, US2008061515 A1, US2008061515A1
InventoresEric Durocher, Rene Paquet, Guy Lefebvre
Cesionario originalEric Durocher, Rene Paquet, Guy Lefebvre
Exportar citaBiBTeX, EndNote, RefMan
Enlaces externos: USPTO, Cesión de USPTO, Espacenet
Rim seal for a gas turbine engine
US 20080061515 A1
Resumen
The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material.
Imágenes(3)
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Reclamaciones(9)
1. A rim seal for an annular space between blade platforms and a non-rotating adjacent structure in a gas turbine engine, the rim seal being connectable to the non-rotating structure and made of an abradable material.
2. The rim seal as defined in claim 1 wherein each blade platform has a side protruding portion in engagement with the abradable material.
3. The rim seal as defined in claim 2 wherein a cold gap is provided between the protruding portion and the rim seal at ambient conditions, the cold gap being designed to close due to thermal expansion during operation of the gas turbine engine.
4. The rim seal as defined in claim 1 wherein the non-rotating structure is made of sheet metal the structure having an end folded radially inwards, the abradable seal being connected to the end.
5. The rim seal as defined in claim 4 wherein the non-rotating structure comprises a seal-holding bracket secured to the end.
6. An annular abradable rim seal for mitigating combustion gas ingestion on a side of blades in a gas turbine engine, the seal having an outer peripheral portion configured and disposed to be at least partially in friction engagement with blade platforms during operation of the engine.
7. The rim seal as defined in claim 6 wherein a cold gap is provided between the blades and the rim seal at ambient conditions, the cold gap being designed to close due to thermal expansion during operation of the gas turbine engine.
8. The rim seal as defined in claim 6 wherein the non-rotating structure comprises a seal-holding bracket secured to a side thereof.
9. A method of sealing an annular space between blade platforms and a non-rotating structure immediately adjacent to the blade platforms in a gas turbine engine, the method comprising:
securing to the non-rotating structure an abradable annular seal provided in the annular space; and
operating the gas turbine engine to carve a notch in the seal with the side of the blades.
Descripción
    TECHNICAL FIELD
  • [0001]
    The invention relates generally to a rim seal for a gas turbine engine, and in particular to a rim seal for use within an annular space between rotating blades and a non-rotating adjacent structure in a gas turbine engine.
  • BACKGROUND
  • [0002]
    In a gas turbine engine, rotating elements, such as compressors and turbine rotors, operate at a very high rotation speed. Their blades are also subjected to intense pressure and heat.
  • [0003]
    Compressors and turbine rotors are mounted between non-rotating structures within the engine. These structures are designed to be as close as possible to the rotating blade platforms. This mitigates pressurized air ingestion inside the gas turbine engine.
  • [0004]
    Although various rim seal arrangements have been suggested in the past, there is always a need to provide an improved rim seal yielding better results than previous seals.
  • SUMMARY
  • [0005]
    In one aspect, the present concept provides a rim seal for an annular space between blade platforms and a non-rotating adjacent structure in a gas turbine engine, the rim seal being connectable to the non-rotating structure and made of an abradable material.
  • [0006]
    In a second aspect, the present concept provides an annular abradable rim seal for mitigating combustion gas ingestion on a side of blades in a gas turbine engine, the seal having an outer peripheral portion configured and disposed to be at least partially in friction engagement with blade platforms during operation of the engine.
  • [0007]
    In a third aspect, the present concept provides a method of sealing an annular space between blade platforms and a non-rotating structure immediately adjacent to the blade platforms in a gas turbine engine, the method comprising securing to the non-rotating structure an abradable annular seal provided in the annular space; and operating the gas turbine engine to carve a notch in the seal with the side of the blades.
  • [0008]
    Further details of these and other aspects of the present invention will be apparent from the detailed description and figures included below.
  • DESCRIPTION OF THE DRAWINGS
  • [0009]
    Reference is now made to the accompanying figures depicting aspects of the present invention, in which:
  • [0010]
    FIG. 1 is a schematic cross-sectional view of an example of a gas turbine engine; and
  • [0011]
    FIG. 2 is a schematic longitudinal cross-sectional view of an example of an improved rim seal.
  • DETAILED DESCRIPTION
  • [0012]
    FIG. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases. In this example, the turbine section 18 includes a high pressure turbine stage 20 and a low pressure turbine stage 22.
  • [0013]
    FIG. 2 schematically shows the downstream side of a turbine wheel disc 24 which can be the rotor of either one of the high pressure turbine stage 20 or the low pressure turbine stage 22. The wheel disc 24 has a plurality of radially interspaced blades 26. In the figure, a blade 26 can be seen having an airfoil section 28 extending radially outwardly from a blade platform 30. A non-rotating structure 32 is present adjacent to the blades 26. The non-rotating structure 32 can be the inner wall of an interturbine duct in the case of the high pressure turbine stage 20 or the inner wall of an exhaust duct in the case of the low pressure turbine stage 22, for example.
  • [0014]
    It should be noted that the improved rim seal is not limited for use with turbine blades or at the outlet of a turbine stage. The rim seal can also be used on either sides of a compressor rotor or on the inlet of the turbine rotor.
  • [0015]
    An annular space 34 is defined immediately adjacent to the blades of the wheel disc 24, between the side of the blade platforms 30 and an end 36 of the non-rotating structure 32. A rim seal 38, connected to the end 36 of the non-rotating structure 32, substantially fills the inner side of the annular space 34. The rim seal 38 is made of an abradable material such as honeycomb-shaped light material, for example.
  • [0016]
    In the illustrated example, each blade platform 26 has a protruding portion 40 on the side thereof. Together, the protruding portion 40 defines an annular recess 42. The rim seal 38 is set within the annular recess 42 along an overlap distance with respect to the edge of the protruding portions 40. A gap 44 referred to as a cold gap 44 is provided between the protruding portions 40 and the rim seal 38 along the overlap distance at ambient conditions. During operation of the gas turbine engine, the temperature rises and causes thermal expansion to close the cold gap 44. A light rub then occurs between the protruding portions 40 and the rim seal 38. This increases the sealing effect. Interference between the rim seal and the protruding portions results in abrasion of the rim seal abradable material and the creation of a notch 46.
  • [0017]
    The relative radial position of the flat portion 48 adjacent the notch 46 can be selected to arrive as flush as possible with the outer surface 50 of the blade platforms 26 and the outer surface 52 of the adjacent non-rotating structure 32 during operation of the engine, to minimize aerodynamic disruptions in the gas flow. A carefully selected flat portion 48 configuration can thus contribute to more closely obtain a smooth surface transition between the outer surface 50 of the blade platform 26 and the outer surface 52 of the non-rotating structure 32. The notch 46 can be machined prior to installation of the rim seal 38. Alternately, it can be carved in the rim seal 38 by abrasion with the protruding portions 40 during engine operation, or can be made by a combination of pre-machining and abrasion during operation.
  • [0018]
    In the illustrated example, a flanged support bracket 54, also made of sheet material, is connected to the end 36 and provides a support flange 56 on which the rim seal 38 can be brazed. The abradable rim seal 38 can be secured both to the flange 56 and to the end 36 of the non-rotating structure 32.
  • [0019]
    The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. For example, the annular rim seal can be used with other types of non-rotating structures than the one described and illustrated herein. Many different types of abradable materials exist and the exact choice thereof is left to those skilled in the art. The seal-holding bracket is optional, many different configurations can be used to connect the abradable rim seal to the edge of the non-rotating structure. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.
Citas de patentes
Patente citada Fecha de presentación Fecha de publicación Solicitante Título
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US6776573 *29 Nov 200117 Ago 2004Snecma MoteursBladed rotor disc side-plate and corresponding arrangement
US6899339 *30 Ago 200131 May 2005United Technologies CorporationAbradable seal having improved durability
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Citada por
Patente citante Fecha de presentación Fecha de publicación Solicitante Título
US8166767 *15 Oct 20101 May 2012Pratt & Whitney Canada Corp.Gas turbine combustor exit duct and hp vane interface
US817251420 Abr 20098 May 2012Pratt & Whitney Canada Corp.Rim seal for a gas turbine engine
US90684691 Sep 201130 Jun 2015Honeywell International Inc.Gas turbine engines with abradable turbine seal assemblies
US98034961 Jul 201531 Oct 2017United Technologies CorporationBreak-in system for gapping and leakage control
US20090110548 *30 Oct 200730 Abr 2009Pratt & Whitney Canada Corp.Abradable rim seal for low pressure turbine stage
US20090208326 *20 Abr 200920 Ago 2009Eric DurocherRim seal for a gas turbine engine
US20110023499 *15 Oct 20103 Feb 2011Nicolas GrivasGas turbine combustor exit duct and hp vane interface
CN101858230A *6 Abr 201013 Oct 2010通用电气公司Methods, systems and/or apparatus relating to seals for turbine engines
EP2239422A3 *31 Mar 201024 May 2017General Electric CompanySeal for a gas turbine engine
EP3112602A1 *1 Jul 20164 Ene 2017United Technologies CorporationBreak-in system for gapping and leakage control
WO2015181489A1 *26 May 20153 Dic 2015SnecmaSealing plate with fuse function
Clasificaciones
Clasificación de EE.UU.277/414, 415/170.1
Clasificación internacionalF04D29/08
Clasificación cooperativaF01D11/122, F01D11/001
Clasificación europeaF01D11/12B, F01D11/00B
Eventos legales
FechaCódigoEventoDescripción
8 Sep 2006ASAssignment
Owner name: PRATT & WHITNEY CANADA CORP., CANADA
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:DUROCHER, ERIC;PAQUET, RENE;LEFEBVRE, GUY;REEL/FRAME:018221/0730
Effective date: 20060908