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Seals and method of manufacture thereof

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Publication number
USRE30206E
USRE30206E US05795668 US79566877A USRE30206E US RE30206 E USRE30206 E US RE30206E US 05795668 US05795668 US 05795668 US 79566877 A US79566877 A US 79566877A US RE30206 E USRE30206 E US RE30206E
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US
Grant status
Grant
Patent type
Prior art keywords
bristles
seal
element
iadd
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.)
Expired - Lifetime
Application number
US05795668
Inventor
John G. Ferguson
Geoffrey D. Waters
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.)
Rolls-Royce PLC
Original Assignee
Rolls-Royce PLC
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Filing date
Publication date
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Classifications

    • AHUMAN NECESSITIES
    • A46BRUSHWARE
    • A46DMANUFACTURE OF BRUSHES
    • A46D3/00Preparing, i.e. Manufacturing brush bodies
    • A46D3/04Machines for inserting or fixing bristles in bodies
    • A46D3/05Machines for inserting or fixing bristles in bodies for fixing the bristles between wires, tapes, or the like
    • AHUMAN NECESSITIES
    • A46BRUSHWARE
    • A46BBRUSHES
    • A46B3/00Brushes characterised by the way in which the bristles are fixed or joined in or on the brush body or carrier
    • A46B3/06Brushes characterised by the way in which the bristles are fixed or joined in or on the brush body or carrier by welding together bristles made of metal wires or plastic materials
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16JPISTONS; CYLINDERS; SEALINGS
    • F16J15/00Sealings
    • F16J15/16Sealings between relatively-moving surfaces
    • F16J15/32Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
    • F16J15/3284Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
    • F16J15/3288Filamentary structures, e.g. brush seals
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00Components
    • F05D2240/55Seals
    • F05D2240/56Brush seals

Abstract

A method of manufacture of an annular seal element comprises the steps of providing an apertured backing ring with closely packed bristles extending radially outwardly from the circumference thereof, clamping the free ends of the bristle between a pair of co-axial rings and welding the rings and the outermost tips of the bristles into a unitary structure and subsequently machining away the original backing ring to leave the rings with radially inwardly extending bristles.
The invention also includes a sealing element made by the method.

Description

This invention relates to seals, and relates in particular to a method of making seal elements and to seal elements made by the method.

In seals between relatively moving parts, there is always a danger of excessive movement of one of the parts towards the other, which can cause severe rubbing contact between the opposite elements of the seal. This is a particular problem in gas turbine engines which have many high speed rotating components carrying seal elements, and rubbing of seals at high speeds can cause excessive heating of the seal elements and even destruction of the seal.

This problem has been tackled in the past, for example, by providing abradable coatings on the static seal element which can be worn away by the rotating seal element. This disadvantage of this solution is that once a rub has occurred, the clearance between the rotating seal element and the worn-away coating is increased and sealing efficiency is lost.

The object of the present invention is to provide a seal which overcomes this disadvantage.

According to the present invention a method of manufacturing a seal element comprises the steps of making a brush having a plurality of tightly packed bristles secured to and projecting from a surface of a backing member, clamping the free ends of the bristles between a pair of clamping members, integrally joining the clamping members and the tips of the bristles, and subsequently removing the backing member and the ends of the bristles attached thereto.

Where the seal element is to form part of a seal between static and rotating structure the original backing member is made as a ring and the bristles may extend either outwardly or inwardly from the ring. The clamping members are also rings and are axially spaced to sandwich the bristles between them.

For gas turbine engine application the bristles will normally be metallic and more specifically for high temperature applications the metal will be a heat resistant metal.

Also according to the invention there is provided a seal including a seal element made according to the method described above.

The invention will now be more particularly described, by way of example only, with reference to the accompanying drawings in which:

FIG. 1 is a sectional elevation of a brush which forms the first stage of the manufacture of a seal element of the present invention,

FIG. 2 is a sectional elevation of the brush of FIG. 1 with the clamping members attached,

FIG. 3 is an end elevation of the brush of FIG. 2,

FIG. 4 is a part of a gas turbine engine showing a typical application of a seal element of the present invention.

Referring now to the drawings in FIG. 1 there is shown a backing ring 1 through which are formed a plurality of holes 3 having a step 5 adjacent their radially inner ends. The left hand side of the figure shows radial holes but on the right-hand side an alternative construction is shown in which the holes 3 are shown to lie at an angle to the radial direction.

The holes are formed as close together as they can possibly be made without breaking into one another and into each hole is pulled a bundle of metallic bristles 6. The bristles are usually straight pieces of small diameter wire i.e. less than 0.005 in diameter and as many as possible are disposed in each of the holes.

The bristles are held in place by a wire lacing which consists of a small diameter copper wire which passes up through one hole, over the central portion of the bent-up bundle of bristles, back down the same hole and up into the next hole, so that all the bundles of bristles are wired together and can be pulled down into their respective holes to seat on the step 5.

The number of bristles projecting outwardly from the holes should be as large as possible and in one example 140 wires of 0.003 in diameter were doubled over and pulled into each hole so that 280 bristles were formed. The diameter of the hole in this example was 0.0625 ins. and the width of the brush produced, i.e. the axial spacing between the clamping rings is 0.10 ins.

The brush construction so far described results in groups of substantially parallel bristles emerging from the holes, but each group is spaced from the next by the wall thickness between the holes. This clearly would not be acceptable for a seal element since the spaces provide a leakage path.

However, at their free ends, the fibres, being not quite parallel, having become intermixed and no spacing such as occurs between the groups at the ring is discernable.

A pair of clamping rings 8 are arranged, one on each side of the brush, and the radially outer ends of the bristles are welded to these rings to form an integral bond. The ring 1 and the wire laced ends of the bristles are then machined away, for example along the dotted line 10 to leave free bristle ends of the desired length protruding from the rings 8.

Provided the initial lengths of wire are sufficiently long to form brush bristles up to 0.75 ins long, the bristles will be sufficiently compact and sufficiently intermixed at their radially outer ends to allow for them to be cut off to approximately 0.25 ins. as the final step. The length of bristle allows sufficient flexibility while allowing also for the bristles to be tightly picked together.

The above described method produces a brush with radially inwardly extending bristles but clearly the method can be applied to the production of a brush having radially outwardly extending bristles. In this case the brush formed initially would be produced with radially inwardly projecting bristles, the radially inner free ends would be clamped and welded and then the original ring and bristle mountings would be machined away to leave radially outwardly projecting bristles.

Clearly also, the seal element formed need not be annular but can be flat, and this can be achieved by making the original brush flat.

The method of joining the bristles to the clamping rings is preferably by welding and a suitable method is the use of an electron beam which is directed at the outer circumference of the bristles and rings. This melts the outer tips of the bristles and the rings to form a weld 12 which integrally unites the bristles and rings. Clearly however, other methods of .Iadd.fusion .Iaddend.joining can be used to produce a similar integral joint, for example, brazing and diffusion bonding.

In order to simplify the joining of the bristles and the rings 8 they are preferably made from the same material, for example, in gas turbine engine seals stainless steel can be used, or for high temperature seals one of the range of nickel based alloys sold under the trade name NIMONIC, is used.

It is also envisaged that the bristles need not be metallic but the method described above is still applicable to non-metallic bristles.

A typical application of a seal element made according to the invention is shown in FIG. 4 in which there are shown two stator stages 20 of a compressor of a gas turbine engine with a rotor stage therebetween. The rotor stage comprises a disc 19 having a plurality of blades 18 mounted on the periphery thereof. Between a flange 24 on the rotor disc 19 and a flange 21 on one of the stators 20 there is formed a seal which comprises a seal element 25 in the form of a brush constructed in accordance with the method of the present invention. The seal element 25 co-operates with the flange 24 to form the complete seal which reduces leakage of air between the rotating and static structures.

The advantages of the seal element of the present invention are that should the flange 24 grow outwardly excessively due to excessive differential thermal expansion during transient running conditions of the engine, contact will be made between the flange 24 and the bristles, but the flexibility and resilience of the bristles will allow them to deflect during such contact so that little wear is produced. After rubbing contact has ended, i.e. when normal engine running conditions are renewed, the bristles will return substantially to their normal position and the sealing clearance will be maintained at a small value.

Another effect of the bristles, is that they do not heat up as quickly as a solid piece of material, as for example in a conventional labyrinth seal. This is partly because the deflection of the bristles reduces the rubbing pressure and partly because, although the bristles are tightly packed there is a tendency for a very small leakage flow of air to pass between the bristles in an axial direction, which will carry some heat generated by the rubbing away with it. Thus there will be less tendency for the heat generated by the rubbing to cause increased thermal expansion of the flange and aggravate the rubbing conditions.

To aid deflection of the bristles, they may be angled in the direction of rotation of the flange 24 by using the alternative method of manufacture described in relation to FIG. 1.

Further, a plurality of seal elements including the bristles may be used in series depending on the degree of sealing required, and to this end a multiple seal element may be made by clamping a second brush between one of the clamping rings of a seal element as described and a third clamping ring, and welding them to the seal element. Further brush elements can be added in this manner as desired.

The brush seal elements may be used either as the static or rotating components of a seal between relatively rotating parts, but preferably the brush seal elements are the static elements to avoid centrifugal effects on the bristles affecting the sealing characteristics. Clearly also brush sealing elements of this type can be used to seal static parts.

One of the clamping rings 8 may have a greater radial depth than the other (as shown in FIG. 4) to resist sideways flexing of the bristles due to a pressure difference across them.

Claims (6)

We claim:
1. A method of manufacturing a seal element comprising the steps of making a brush having a plurality of tightly packed bristles secured to and projecting from a surface of a backing member, clamping the free ends of the bristles between a pair of clamping members, integrally .[.joining.]. .Iadd.fusing .Iaddend.the clamping members and the tips of the bristles, and subsequently removing the backing member and the ends of the bristles attached thereto.
2. A method according to claim 1 and in which the bristles and clamping rings are metallic and are integrally .[.joined.]. .Iadd.fused .Iaddend.by welding, brazing of diffusion bonding.
3. A method according to claim 1 and wherein the bristles are made to project at an angle to the surface of the backing member, whereby in the finished seal element, the bristles project at an angle from the clamping members.
4. A method according to claim 1 and wherein the backing member is annular and the bristles project radially from the radially inner circumferential surface thereof, and the clamping members are co-axial rings which clamp the free radially outer ends of the bristles whereby the resulting seal element is annular and has radially inwardly extending bristles.
5. A method according to claim 1 and wherein the backing member is annular and the bristles project radially from the radially outer circumferential surface thereof, and the clamping members are co-axial rings which clamp the free radially outer ends of the bristles whereby the resulting seal element is annular and has radially inwardly extending bristles.
6. A seal element manufactured by the .[.method according to claim 1.]. .Iadd.steps comprising making a brush having a plurality of tightly packed bristles secured to and projecting from a surface of a backing member, clamping the free ends of the bristles between a pair of clamping members, integrally fusing the clamping members and the tips of the bristles and subsequently removing the backing member and the ends of the bristles attached thereto.Iaddend.. .Iadd. 7. A gas sealing element for reducing leakage of gas between two parts of a fluid flow machine, said element comprising an annular array of tightly-packed bristles sandwiched between a pair of side-plates and integrally fused therewith, said bristles projecting from between the side-plates with a circumferential component of direction. .Iaddend..Iadd. 8. A gas sealing element as claimed in claim 7, and in which the side-plates are annular and the bristles project in a generally radial direction. .Iaddend. .Iadd. 9. A gas sealing element as claimed in claim 8 and in which one of the side-plates has a greater radial depth than the other. .Iaddend..Iadd. 10. A gas sealing element as claimed in claim 9 and in which the bristles project radially inwardly from the inner circumferential side edges of the side-plates. .Iaddend. .Iadd. 11. A gas sealing element as claimed in claim 10 and in which the bristles are metallic. .Iaddend..Iadd. 12. A gas sealing element as claimed in claim 11 and in which the bristles are welded to the side-plates at the radially outer circumferential side edges of the side-plates. .Iaddend..Iadd. 13. A gas sealing element as claimed in claim 9 and in which the bristles project radially outwardly from the outer circumferential side edges of the side-plates. .Iaddend. .Iadd. 14. A combination of a gas sealing element and a fluid flow machine, the gas sealing element for reducing leakage of gas between two parts of the fluid flow machine, said sealing element comprising that claimed in claim 7 wherein the side plates are connected to one of the parts and the bristles extend into contiguous relationship with the other of the parts to effect a seal. .Iaddend. .Iadd. 15. A combination as claimed in claim 14 and in which one of the parts is rotatable, and the other part is static, the sealing element being connected to the static part, with the bristles oriented in the direction of rotation of the rotating part. .Iaddend..Iadd. 16. A combination as claimed in claim 15 and in which the sealing element is annular, and the bristles project in a generally radial direction from the entire circumference thereof. .Iaddend..Iadd. 17. A combination as claimed in claim 16 and in which the rotatable part includes a circumferential flange, and said bristles extend into contiguous relationship with said flange. .Iaddend..Iadd. 18. A combination as claimed in claim 17 and in which the bristles extend generally radially inwardly from said static part. .Iaddend..Iadd. 19. A combination as claimed in claim 17 and in which the bristles extend generally radially outwardly from said static part. .Iaddend..Iadd. 20. A combination as claimed in claim 16 and in which one of the side-plates has a greater radial depth than the other for thereby resisting flexing of the bristles due to a pressure difference across the seal. .Iaddend..Iadd. 21. A combination as claimed in claim 14 and in which the bristles are metallic. .Iaddend. .Iadd. 22. A gas turbine apparatus including two parts across which exists a gas pressure difference, and a gas seal for reducing leakage of gas between the two parts said seal comprising a sealing element as claimed in claim 7 wherein the side plates are connected to one of the parts and the bristles extend into contiguous relationship with the other of the parts to effect a seal. .Iaddend. .Iadd. 23. A gas turbine apparatus as claimed in claim 22 and in which one of the two parts is rotatable, and the other part is static, the sealing element being connected to the static part, with the bristles oriented in the direction of rotation of the rotating part. .Iaddend..Iadd. 24. A gas turbine apparatus as claimed in claim 23 and in which the sealing element is connected to the static part, the rotatable part includes a circumferential flange, and said bristles extend into contiguous relationship with said flange. .Iaddend..Iadd. 25. A gas turbine apparatus as claimed in claim 24 and in which the bristles extend generally radially outwardly from the static part. .Iaddend..Iadd. 26. A gas turbine apparatus as claimed in claim 24 and in which the bristles extend generally radially outwardly from the static part. .Iaddend..Iadd. 27. A gas turbine apparatus as claimed in claim 22 and in which one of the side-plates extends further along the lengths of the bristles towards the free ends thereof than the other side-plate for resisting flexing of the bristles under said pressure difference. .Iaddend..Iadd. 28. A gas turbine apparatus as claimed in claim 27 and in which the bristles are metallic. .Iaddend.
US05795668 1973-11-23 1977-05-10 Seals and method of manufacture thereof Expired - Lifetime USRE30206E (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB54518/73 1973-11-23
GB5451873A GB1450553A (en) 1973-11-23 1973-11-23 Seals and a method of manufacture thereof
US3917150A US3917150A (en) 1973-11-23 1974-11-15 Seals and method of manufacture thereof
US05795668 USRE30206E (en) 1973-11-23 1977-05-10 Seals and method of manufacture thereof

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Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0192477A2 (en) * 1985-02-20 1986-08-27 ROLLS-ROYCE plc Brush seals
EP0199322A1 (en) * 1985-04-20 1986-10-29 Mtu Motoren- Und Turbinen-Union München Gmbh Brush seal
EP0199320A1 (en) * 1985-04-20 1986-10-29 Mtu Motoren- Und Turbinen-Union München Gmbh Heat exchanger
EP0211275A2 (en) * 1985-07-31 1987-02-25 Mtu Motoren- Und Turbinen-Union München Gmbh Method and apparatus for manufacturing brush seals
EP0355649A2 (en) * 1988-08-20 1990-02-28 Mtu Motoren- Und Turbinen-Union München Gmbh Sealing device
US4989886A (en) * 1988-12-30 1991-02-05 Textron Inc. Braided filamentary sealing element
US4989919A (en) * 1988-08-30 1991-02-05 Pratt & Whitney Canada Method and apparatus for manufacturing compliant brush seals
US5029875A (en) * 1989-07-07 1991-07-09 Textron Inc. Fluid seal structure
US5031922A (en) * 1989-12-21 1991-07-16 Allied-Signal Inc. Bidirectional finger seal
US5071138A (en) * 1989-12-21 1991-12-10 Allied-Signal Inc. Laminated finger seal
US5074748A (en) * 1990-07-30 1991-12-24 General Electric Company Seal assembly for segmented turbine engine structures
US5108116A (en) * 1991-05-31 1992-04-28 Allied-Signal Inc. Laminated finger seal with logarithmic curvature
US5110033A (en) * 1991-02-21 1992-05-05 United Technologies Corporation Segmented brush seal
US5135237A (en) * 1989-04-05 1992-08-04 Cross Manufacturing Company (1938) Limited Brush seal with asymmetrical elements
US5165758A (en) * 1991-08-07 1992-11-24 Technetics Corporation Place and bundle method for the manufacture of brush seals
US5183197A (en) * 1991-08-07 1993-02-02 Technetics Corp. Bundle and place method for the manufacture of brush seals
USRE34398E (en) * 1988-04-05 1993-10-05 Rolls-Royce Plc Apparatus for and method of manufacturing brush seals
US5308088A (en) * 1992-08-20 1994-05-03 General Electric Company Brush seal with flexible backing plate
US5318309A (en) * 1992-05-11 1994-06-07 General Electric Company Brush seal
US5335920A (en) * 1992-08-20 1994-08-09 General Electric Company Brush seal
US5498139A (en) * 1994-11-09 1996-03-12 United Technologies Corporation Brush seal
US5568931A (en) * 1992-08-20 1996-10-29 General Electric Company Brush seal
US6231047B1 (en) * 1998-05-29 2001-05-15 Eg&G Engineered Products Brush seal
US6364316B1 (en) 1999-02-11 2002-04-02 Honeywell International Inc. Dual pressure balanced noncontacting finger seal
US6457719B1 (en) 2000-08-14 2002-10-01 United Technologies Corporation Brush seal
US6488471B1 (en) * 2000-10-04 2002-12-03 The United States Of America As Represented By The Secretary Of The Air Force Gas-turbine brush seals with permanent radial gap
US6508624B2 (en) 2001-05-02 2003-01-21 Siemens Automotive, Inc. Turbomachine with double-faced rotor-shroud seal structure
US20030062684A1 (en) * 2001-09-28 2003-04-03 Eagle Industry Co., Ltd. Brush seal
US6736401B2 (en) 2001-12-19 2004-05-18 Honeywell International, Inc. Laminated finger seal with ceramic composition
US20040119237A1 (en) * 2000-08-09 2004-06-24 Amitava Datta Brush seal assembly, method of manufacture and use
US20050146095A1 (en) * 2002-03-26 2005-07-07 Siemens Aktiengesellschaft Sealing assembly for a spindle
US20050194747A1 (en) * 2004-01-28 2005-09-08 Rolls-Royce Plc Sealing arrangement
US20070120326A1 (en) * 2004-03-30 2007-05-31 Alstom Technology Ltd. Leaf seal, in particular for a gas turbine, and method of producing it
US20070214628A1 (en) * 2006-03-17 2007-09-20 General Electric Company Methods of manufacturing a segmented brush seal for sealing between stationary and rotary components
US20080007008A1 (en) * 2004-12-11 2008-01-10 Alstom Technology Ltd Leaf seal, in particular for a gas turbine
US20130170979A1 (en) * 2012-01-04 2013-07-04 General Electric Company Double ended brush seal assembly for a compressor

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US885032A (en) * 1907-06-24 1908-04-21 Sebastian Ziani De Ferranti Fluid packing.
US1713027A (en) * 1925-04-22 1929-05-14 William H Doble Wire brush
US2672640A (en) * 1945-05-23 1954-03-23 Osborn Mfg Co Brush and method of making same
US2878048A (en) * 1954-03-18 1959-03-17 Osborn Mfg Co Brush seal and the like
GB839731A (en) 1957-09-19 1960-06-29 Bendix Aviat Corp Sealing arrangement for bearing assemblies
US3050891A (en) * 1959-04-27 1962-08-28 Richard N Thomsen Artificial tree branches
US3239276A (en) * 1961-09-25 1966-03-08 Osborn Mfg Co Method of manufacturing composite brushing tools
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Cited By (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0192477A3 (en) * 1985-02-20 1987-09-30 ROLLS-ROYCE plc Brush seals
EP0192477A2 (en) * 1985-02-20 1986-08-27 ROLLS-ROYCE plc Brush seals
EP0199322A1 (en) * 1985-04-20 1986-10-29 Mtu Motoren- Und Turbinen-Union München Gmbh Brush seal
EP0199320A1 (en) * 1985-04-20 1986-10-29 Mtu Motoren- Und Turbinen-Union München Gmbh Heat exchanger
EP0211275A2 (en) * 1985-07-31 1987-02-25 Mtu Motoren- Und Turbinen-Union München Gmbh Method and apparatus for manufacturing brush seals
EP0211275A3 (en) * 1985-07-31 1988-01-20 Mtu Muenchen Gmbh Method and apparatus for manufacturing brush seals
USRE34398E (en) * 1988-04-05 1993-10-05 Rolls-Royce Plc Apparatus for and method of manufacturing brush seals
US5026252A (en) * 1988-08-20 1991-06-25 Mtu Motoren- Und Turbinen- Union Munchen Gmbh Sealing device for turbo engines and the like
EP0355649A2 (en) * 1988-08-20 1990-02-28 Mtu Motoren- Und Turbinen-Union München Gmbh Sealing device
EP0355649A3 (en) * 1988-08-20 1990-09-26 Mtu Muenchen Gmbh Sealing device
US4989919A (en) * 1988-08-30 1991-02-05 Pratt & Whitney Canada Method and apparatus for manufacturing compliant brush seals
US4989886A (en) * 1988-12-30 1991-02-05 Textron Inc. Braided filamentary sealing element
US5135237A (en) * 1989-04-05 1992-08-04 Cross Manufacturing Company (1938) Limited Brush seal with asymmetrical elements
US5029875A (en) * 1989-07-07 1991-07-09 Textron Inc. Fluid seal structure
US5071138A (en) * 1989-12-21 1991-12-10 Allied-Signal Inc. Laminated finger seal
US5031922A (en) * 1989-12-21 1991-07-16 Allied-Signal Inc. Bidirectional finger seal
US5074748A (en) * 1990-07-30 1991-12-24 General Electric Company Seal assembly for segmented turbine engine structures
US5110033A (en) * 1991-02-21 1992-05-05 United Technologies Corporation Segmented brush seal
US5108116A (en) * 1991-05-31 1992-04-28 Allied-Signal Inc. Laminated finger seal with logarithmic curvature
US5165758A (en) * 1991-08-07 1992-11-24 Technetics Corporation Place and bundle method for the manufacture of brush seals
US5183197A (en) * 1991-08-07 1993-02-02 Technetics Corp. Bundle and place method for the manufacture of brush seals
US5318309A (en) * 1992-05-11 1994-06-07 General Electric Company Brush seal
US5308088A (en) * 1992-08-20 1994-05-03 General Electric Company Brush seal with flexible backing plate
US5568931A (en) * 1992-08-20 1996-10-29 General Electric Company Brush seal
US5335920A (en) * 1992-08-20 1994-08-09 General Electric Company Brush seal
US5498139A (en) * 1994-11-09 1996-03-12 United Technologies Corporation Brush seal
US6231047B1 (en) * 1998-05-29 2001-05-15 Eg&G Engineered Products Brush seal
US6364316B1 (en) 1999-02-11 2002-04-02 Honeywell International Inc. Dual pressure balanced noncontacting finger seal
US20040119237A1 (en) * 2000-08-09 2004-06-24 Amitava Datta Brush seal assembly, method of manufacture and use
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