EP0081010A2 - Unterbrochene Wabenstruktur - Google Patents

Unterbrochene Wabenstruktur Download PDF

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Publication number
EP0081010A2
EP0081010A2 EP81304682A EP81304682A EP0081010A2 EP 0081010 A2 EP0081010 A2 EP 0081010A2 EP 81304682 A EP81304682 A EP 81304682A EP 81304682 A EP81304682 A EP 81304682A EP 0081010 A2 EP0081010 A2 EP 0081010A2
Authority
EP
European Patent Office
Prior art keywords
panel
cells
walls
honeycomb
strip
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Withdrawn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
EP81304682A
Other languages
English (en)
French (fr)
Other versions
EP0081010A3 (de
Inventor
George T. Straza
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP0081010A2 publication Critical patent/EP0081010A2/de
Publication of EP0081010A3 publication Critical patent/EP0081010A3/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Withdrawn legal-status Critical Current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
    • F01D11/08—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
    • F01D11/127—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 a deformable or crushable structure, e.g. honeycomb
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb

Definitions

  • Honeycomb core material is used in a variety of structures for strength and rigidity with minimum weight. Most honeycomb structures, particularly metal types, are built up from corrugated strips assembled in parallel longitudinal alignment and secured together at confronting walls of the corrugations by spot welding, or similar means. The resultant structure has rows of open cells extending through the thickness of the panel between opposite faces. In a complete structural assembly, one or both faces of the honeycomb may be bonded to a backing or cover panel of sheet material, by brazing, adhesive, or other such bonding means.
  • honeycomb material is iri a turbojet engine or the like.
  • peripheral clearance between the moving blade tips and their surrounding duct sections must be kept to a minimum. Due to heat and centrifugal force, the blades tend to creep or expand radially and the blade tips may strike the duct wall, unless the initial clearance is sufficient to allow for this. Excessive clearance is undesirable, but the blades may be damaged by striking the duct.
  • certain duct sections have been lined with a material which can be deformed by a limited amount of blade contact without damaging the blades.
  • Honeycomb material with an open face confronting the moving blades has been used satisfactorily and will allow the blades to wipe against the open cell face without damage. However, the contamination of the open cell face by bonding material, particularly hard braze, defeats the purpose and could cause chipping or abrading of the blades, leading to more severe damage.
  • honeycomb structure described herein is constructed in such a manner that one face can be enclosed without the bonding material contaminating the open face.
  • Strips of corrugated material are secured together in the conventional manner, to form a honeycomb structur.e with rows of cells extending through the thickness of the panel between the opposite faces.
  • the corrugated strips are prepared, however, by restricting the corrugations so that, in the assembled structure, the cells are not continuous through the panel.
  • the cells can be alternately staggered at opposite faces of the panel to break continuity, or can be basically continuous between the faces, the restriction being made by pinching the cells to reduce or block their open cross sections.
  • the primary object of this invention is to provide a new and improved interrupted cell honeycomb structure.
  • Another object of this invention is to provide a honeycomb structure in which the cells are restricted between the faces to separate the confronting cells walls and restrict the cell cross section.
  • a further object of this invention is to provide a restricted cell honeycomb structure which can be assembled by conventional apparatus and techniques, the novel restricted cell configuration being incorporated in the initial preparation of the corrugated strips.
  • the honeycomb structure is composed of a plurality of corrugated strips 10, illustrated in a preferred form in Figure 1.
  • the strips are made by passing thin sheet metal or other such material, between interfitting toothed rollers, having teeth corresponding to the required cell cross section.
  • the cells are hexagonal but could be of square or other cross sectional configuration.
  • the strip 10, has alternately offset or staggered side walls 12 and 14 connected by diagonal walls 16, the overall depth of the corrugated strip being half the width of a cell. Walls 12 are in one common plane and walls 14 are in another common plane, the planes being separated by the depth of the strip.
  • the strips are joined at confronting walls in back to back pairs, with the walls 12 along one side of one strip attached, to the walls 12 of the adjacent strip, as in Figure 2, consecutive strips being assembled to produce a honeycomb panel of the required size.
  • the next pair is joined to the first pair at walls 14, the panel being built up to the required width.
  • the conventional method of joining is by spot welding the confronting walls at one or more locations on each joined area.
  • the walls are thus bonded together only at spots, rather than over the entire contacting area.
  • this spot joining is sufficient.
  • one or both faces of the honeycomb structure will be enclosed by bonding a backing or cover panel to the end edges of the cells.
  • this is normally accomplished by brazing, with a brazing material applied to the edges of the cell structure and the cover panel heat sealed in place.
  • One well known technique uses tape impregnated with brazing material in powder form, the tape burning and gassing off when heated and the powder melting and forming the bond.
  • brazing material tends to flow over the cell surfaces as indicated at 18 in Figure 7 and, in particular, is drawn between the confronting walls by capillary action.
  • the bonding material can thus wick to the opposite face of the honeycomb.
  • the cells are longitudinally staggered along opposite edges, so that there is no cell extending completely through the panel.
  • Cells 20 are spaced along one side or face of the panel and cells 22 along the other face.
  • Cells 20 have closed inner ends 24 which are aligned with the spaces between cells 22, while cells 22 have closed inner ends 26 aligned with the spaces between cells 20.
  • the closed ends are formed by pinching and inclining portions of side walls 12 toward walls 14.
  • the cells 22 are shown as being several times the length of cells 20, the closed ends being close to one face of the panel.
  • the backing or cover panel 28, indicated in broken line in Figures 3 and 4 would be secured by brazing to the outer edges of cells 20. This limits the spread of the brazing material to the short length of cells 20, leaving cells 22 free of braze.
  • honeycomb material can be made in various sizes, but one particular size developed for a specific purpose will emphasize the need for solving the problem of contamination by bonding material.
  • the honeycomb panel has a depth of about 6 mm between faces, with hexagonal cells about 1.5 mm across the flats. This very small size is particularly susceptible to braze contamination of the open face.
  • the openings 30 allow the use of one well known technique for testing the quality of braze to the cover panel, which is not possible to inspect visually through the very small cells.
  • this technique a very free flowing liquid is injected into one or more cells in an area where poor braze is suspected. If the braze is incomplete the liquid will leak long the inside of the cover plate and appear in other cells, indicating the fault in the braze.
  • Ultrasonic, x-ray and other conventional inspection techniques may also be used.
  • the open faced honeycomb is shown in a specific use in Figures 8 and 9, in which the material is used to line the interior of a duct section 32 of a turbojet engine.
  • the turbine rotor 34 has blades 36 which are required to have a minimum tip clearance from the duct wall to prevent tip losses and maintain efficiency. Under excessive centrifugal loads and high temperatures the blades can expand or creep radially and strike the duct wall, resulting in damage to the blades and duct. To minimize blade damage under these conditions a technique has been developed in which the duct is lined with a deformable material which can absorb blade contact while maintaining a good seal.
  • the open face honeycomb material has been found especially suitable for this purpose since the cellular structure can be struck and deformed by the blades, yet the multi-cellular body, even when partially crushed, will form a labyrinth to minimize gas leakage and tip losses. It has been found, however, that braze contamination of the open face cells can make the material harder than desired in contaminated areas, resulting in chipping of the blades and possible shedding of material from the honeycomb.
  • honeycomb is thus installed in segments inside the duct 32 to form a lining 38.
  • the outer face of the honeycomb material is bonded to a cover strip 40, by which the material is suitably secured to the duct, the open cell, braze free inner face 42 being adjacent to the blade tips. Under high stress conditions, the blades can thus rub on the honeycomb lining without damage.
  • honeycomb material with cells of equal length, as in the corrugated strip 44 in Figure 5. All features are as described for strip 10, except that the cells 46 at one side and the cells 48 at the other side are of substantially equal length.
  • This configuration is particularly suitable for enclosed type honeycomb panels with cover panels brazed to both sides.
  • Such panels have been used as outer skin members of aircraft for structural lightness, strength and insulation.
  • the honeycomb panel may be the outer shell of a fuel tank integral with a wing or fuselage component of an aircraft. At high speeds the skin is heated by friction and could cause vaporization or even boiling of the fuel, so thermal insulation is necessary. Honeycomb material will provide such insulation if the thermal conductivity through the panel can be minimized.
  • braze material Since the thermal conductivity of braze material is much higher than that of the stainless steel, or similar material used to make the honeycomb, it is necessary to prevent a conductive path of braze material through the panel.
  • the interrupted cell arrangement effectively prevents such a thermally conductive path by controlling the migration of braze material.
  • Corrugated strip i10 has cells 52 along one side and cells 54 along the other side, the cells having confronting closed ends 56 and 58, respectively. Between the cells are flat walls 60 which extend across the width of the strip. To avoid any continuous capillary paths through the honeycomb the strips are joined with the flat walls 60 of one strip secured to the interrupted walls 62 of the next adjacent strip.
  • This configuration is also suitable for single or double sided enclosure with no braze migration through the panel.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Laminated Bodies (AREA)
  • Exhaust Gas After Treatment (AREA)
EP81304682A 1981-08-10 1981-10-08 Unterbrochene Wabenstruktur Withdrawn EP0081010A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US29073081A 1981-08-10 1981-08-10
US290730 1981-08-10

Publications (2)

Publication Number Publication Date
EP0081010A2 true EP0081010A2 (de) 1983-06-15
EP0081010A3 EP0081010A3 (de) 1983-08-03

Family

ID=23117308

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81304682A Withdrawn EP0081010A3 (de) 1981-08-10 1981-10-08 Unterbrochene Wabenstruktur

Country Status (3)

Country Link
EP (1) EP0081010A3 (de)
JP (1) JPS5825953A (de)
IL (1) IL64132A0 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3135869A1 (de) * 2015-08-25 2017-03-01 Rolls-Royce Deutschland Ltd & Co KG Dichtelement für eine turbomaschine zugehörige turbomaschine und herstellungsverfahren
FR3112165A1 (fr) * 2020-07-01 2022-01-07 Safran Aircraft Engines Dispositif abradable d’étanchéité

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0733444Y2 (ja) * 1986-12-04 1995-07-31 三菱電機株式会社 サスペンデツド線路
JP5852804B2 (ja) * 2011-08-04 2016-02-03 岐阜プラスチック工業株式会社 合成樹脂構造体

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US220596A (en) * 1879-10-14 Improvement in billiard-cue-coloring apparatus
US2858247A (en) * 1955-08-04 1958-10-28 Swart Dev Company De Panel material
US3423070A (en) * 1966-11-23 1969-01-21 Gen Electric Sealing means for turbomachinery
GB2001692A (en) * 1977-07-29 1979-02-07 Rolls Royce Honeycomb structures: gas turbines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US220596A (en) * 1879-10-14 Improvement in billiard-cue-coloring apparatus
US2858247A (en) * 1955-08-04 1958-10-28 Swart Dev Company De Panel material
US3423070A (en) * 1966-11-23 1969-01-21 Gen Electric Sealing means for turbomachinery
GB2001692A (en) * 1977-07-29 1979-02-07 Rolls Royce Honeycomb structures: gas turbines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3135869A1 (de) * 2015-08-25 2017-03-01 Rolls-Royce Deutschland Ltd & Co KG Dichtelement für eine turbomaschine zugehörige turbomaschine und herstellungsverfahren
US10480340B2 (en) 2015-08-25 2019-11-19 Rolls-Royce Deutschland Ltd & Co Kg Sealing element for a turbo-machine, turbo-machine comprising a sealing element and method for manufacturing a sealing element
FR3112165A1 (fr) * 2020-07-01 2022-01-07 Safran Aircraft Engines Dispositif abradable d’étanchéité

Also Published As

Publication number Publication date
EP0081010A3 (de) 1983-08-03
JPS5825953A (ja) 1983-02-16
IL64132A0 (en) 1982-01-31

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