EP2312125A1 - Verkleidungsdichtung - Google Patents

Verkleidungsdichtung Download PDF

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Publication number
EP2312125A1
EP2312125A1 EP09173250A EP09173250A EP2312125A1 EP 2312125 A1 EP2312125 A1 EP 2312125A1 EP 09173250 A EP09173250 A EP 09173250A EP 09173250 A EP09173250 A EP 09173250A EP 2312125 A1 EP2312125 A1 EP 2312125A1
Authority
EP
European Patent Office
Prior art keywords
seal
fairing
stator assembly
edge portion
vane
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Withdrawn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
EP09173250A
Other languages
English (en)
French (fr)
Inventor
Courtney James Tudor
Scott Alan Garten
Eli B. Kalaani
Samir Mahendra Mehta
Steven Edward Dinser
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to EP09173250A priority Critical patent/EP2312125A1/de
Publication of EP2312125A1 publication Critical patent/EP2312125A1/de
Withdrawn legal-status Critical Current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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms

Definitions

  • This invention relates generally to seals for reducing leakage of a fluid, and more specifically to integrated seals in fairings used in gas turbine engines and methods of manufacturing fairings having integrated seals.
  • FIG. 1 illustrates, for example, a bypass airflow 2 in a fan module and a core airflow 3 in a low pressure compressor (booster) module.
  • Compressed air is mixed with fuel in a combustor and ignited, generating hot combustion gases which flow through turbine stages that extract energy therefrom for powering the fan and compressor rotors and generate engine thrust to propel an aircraft in flight.
  • Engine frames are used to support and carry the bearings which, in turn, rotatably support the rotors.
  • Conventional turbofan engines have a fan frame, a mid-frame, and an aft turbine frame. Such frames may have an external casing and an internal hub which are attached to each other through a plurality of multiple radially extending struts that extend through the flowpath.
  • Flowpath liner and fairing assemblies provide a flowpath that guides and directs the gases flowing through the frame.
  • the stator assemblies have segmented fairings that are arranged circumferentially wherein vanes or struts extend between circumferentially adjacent fairing segments.
  • a strut or a vane that extends radially through a flowpath is referred to herein as outlet guide vane ("OGV").
  • OGVs may, in some applications, reorient the flow in the flowpath to a more axial direction.
  • FIG. 2 shows a conventional assembly of two conventional fairings 30 adjacent to an OGV 22 that extends radially between them.
  • FIG. 2 illustrates some of the problems that may exist in using conventional stator assemblies 35 having the conventional fairings 30.
  • the conventional stator assembly 35 has an axial gap 32 located at the interface between two adjacent conventional fairings 30.
  • An axial gap 34 also exists at the interface between the OGV 22 and the two adjacent conventional fairings 30.
  • These axial gaps 32, 34 cause leakage of a portion of the fluid flowing over the conventional fairings 30, such as the leakage of bypass airflow 2 from the flowpath, leading to a performance loss in the engine.
  • the performance loss is further aggravated by the fact that, in some designs, the OGVs may have different geometries at different circumferential locations and result in conventional fairings 30 having axial gaps 34 that vary at these different circumferential locations.
  • the first fairing 81 is located circumferentially very close to the vane 22 such that the first seal 61 reduces the axial gap between the first seal 61 and the first side of vane 22.
  • the first seal 61 may be brought into contact with the first side 25 of the vane 22 such that the axial gap between the first seal 61 and the first side of vane 22 may be eliminated at those locations where such contact is established.
  • the second fairing 82 is located circumferentially very close to the vane 22 such that the second seal 62 reduces the axial gap between the second seal 62 and the second side of vane 22.
  • the first fairing 81 and second fairing 82 are assembled such that the first seal 61 and the second seal 62 also interface with each other at axial locations away from the vane 22.
  • the first fairing 81 and second fairing 82 are assembled such that at locations axially forward and axially aft from the vane 22, the first seal 61 is circumferentially very close to the second seal 62 and reduce the axial gap between them.
  • the axial gap may be eliminated at some axial locations wherein the first seal 61 overlaps with the second seal 62, such as, for example, shown in FIG. 6 and explained subsequently herein.
  • FIG. 6 shows a schematic cross-sectional view of two adjacent components 71, 72 sealingly engaged with each other, according to an exemplary embodiment of the present invention.
  • the two adjacent components 71, 72 may be, in one example, the first fairing 81 having a first seal 61 and the second fairing 82 having a second seal 62, shown in FIG. 3 .
  • FIG. 6 shows a cross-section of the interface between two fairings 81, 82, having the two adjacent seals 61, 62 after assembly, such as in a stator assembly 80.
  • the contact faces 52 of the two seals 61, 62 are engaged such that there is no gap between the seals, providing full sealing.
  • FIG. 7 shows a schematic cross-sectional view of an alternative exemplary embodiment 100 of the present invention, showing two adjacent components 71, 72 having seals 101, 102.
  • the seals 101, 102 have a cavity profile 103 that is generally circular in shape. Other suitable cavity profile shapes may also be used.
  • a notable feature of the seals 101, 102 shown in FIG. 7 is that the contact face that provides sealing is non-planar.
  • a non-planar contact face, such as shown for example in FIG. 7 provides advantages in some applications, such as, for example, in cases involving significant movements between the two adjacent components 71, 72.
  • the seal 101 has support flanges 154, 155 that are used for mounting the seal 101 to the first component 71. Methods of mounting and bonding a seal to a fairing as described herein can be used to couple each seal 101, 102 with the corresponding component 71, 72.
  • FIG. 9 shows a schematic cross-sectional view of another alternative exemplary embodiment 130 of the present invention, showing two adjacent components 71, 72 having seals 131, 132.
  • the seals 131, 132 do not have a cavity inside.
  • the first seal 131 has a single support flange 135.
  • the second seal 132 has a different geometry from the first seal 131, and has a single support flange 136.
  • the contact face 137 is planar.
  • the axial edges are preferably machined to have a suitable contour corresponding to the contours of an adjacent component during assembly, such as for example, a vane 22 in a stator assembly 80.
  • the method 500 further comprises the step 520 of supplying a seal 50, such as, for example shown in FIGS. 5-10 and described previously herein.
  • the method 500 comprises a step 535 of applying a pressure sensitive adhesive (PSA) tape to the component surface 43 or the seal 50.
  • PSA pressure sensitive adhesive
  • a double sided PSA tape may be used to hold the seal 50 in place during mounting.
  • the PSA is preferably used on the side of the fairing that is opposite to the flow path side.
  • the method 500 further comprises the step 545 of mounting the seal 50 to the component 40.
  • the flanges 54, 55 of the seal 50 are mounted on the edge portion 41 of the component, such as the fairing 40.
  • the seal 50 and the fairing 40 may be optionally clamped together using a suitable clamping fixture in order to provide intimate contact during bonding between the seal 50 and the fairing 40.
  • the bond material 48 between the seal 50 and the edge portion 41 is cured.
  • Silicone RTV is used for bonding, curing may be completed in about 7 days. The bonds cure sufficiently for handling in about 24 hours. Other known methods may also be used for curing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09173250A 2009-10-16 2009-10-16 Verkleidungsdichtung Withdrawn EP2312125A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09173250A EP2312125A1 (de) 2009-10-16 2009-10-16 Verkleidungsdichtung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09173250A EP2312125A1 (de) 2009-10-16 2009-10-16 Verkleidungsdichtung

Publications (1)

Publication Number Publication Date
EP2312125A1 true EP2312125A1 (de) 2011-04-20

Family

ID=42062284

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09173250A Withdrawn EP2312125A1 (de) 2009-10-16 2009-10-16 Verkleidungsdichtung

Country Status (1)

Country Link
EP (1) EP2312125A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2615246A1 (de) * 2012-01-16 2013-07-17 MTU Aero Engines GmbH Leitschaufelring, Leitschaufelsegment, Verfahren zur Herstellung eines Leitschaufelsegments sowie eine Strömungsmaschine
WO2015053848A2 (en) 2013-09-18 2015-04-16 United Technologies Corporation Fan platform with leading edge tab
EP2623720A3 (de) * 2012-02-02 2018-04-11 Honeywell International Inc. Verfahren zur geregelten Verringerung der Durchströmbereiche einer Turbinendüse und Turbinendüsenkomponenten mit verringerten Durchströmbereichen

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB802508A (en) * 1955-07-18 1958-10-08 Rolls Royce Improvements in or relating to fluid machines such as compressors and turbines
US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
EP0787890A2 (de) * 1996-02-02 1997-08-06 ROLLS-ROYCE plc Gasturbinenrotor
EP1067274A1 (de) * 1999-07-06 2001-01-10 Rolls-Royce Plc Rotordichtung
EP1865154A1 (de) * 2006-06-06 2007-12-12 Rolls-Royce plc Schaufelreihe und Dichtung für den Schaufelzwischenraum
EP1881160A2 (de) * 2006-07-22 2008-01-23 Rolls-Royce plc Abdichtung für eine Plattform zwischen Fanschaufeln

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB802508A (en) * 1955-07-18 1958-10-08 Rolls Royce Improvements in or relating to fluid machines such as compressors and turbines
US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
EP0787890A2 (de) * 1996-02-02 1997-08-06 ROLLS-ROYCE plc Gasturbinenrotor
EP1067274A1 (de) * 1999-07-06 2001-01-10 Rolls-Royce Plc Rotordichtung
EP1865154A1 (de) * 2006-06-06 2007-12-12 Rolls-Royce plc Schaufelreihe und Dichtung für den Schaufelzwischenraum
EP1881160A2 (de) * 2006-07-22 2008-01-23 Rolls-Royce plc Abdichtung für eine Plattform zwischen Fanschaufeln

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2615246A1 (de) * 2012-01-16 2013-07-17 MTU Aero Engines GmbH Leitschaufelring, Leitschaufelsegment, Verfahren zur Herstellung eines Leitschaufelsegments sowie eine Strömungsmaschine
EP2623720A3 (de) * 2012-02-02 2018-04-11 Honeywell International Inc. Verfahren zur geregelten Verringerung der Durchströmbereiche einer Turbinendüse und Turbinendüsenkomponenten mit verringerten Durchströmbereichen
WO2015053848A2 (en) 2013-09-18 2015-04-16 United Technologies Corporation Fan platform with leading edge tab
EP3047109A4 (de) * 2013-09-18 2016-10-05 United Technologies Corp Gebläseplattform mit anströmkantenlasche
US10227884B2 (en) 2013-09-18 2019-03-12 United Technologies Corporation Fan platform with leading edge tab

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