US20110182721A1 - Sealing arrangement for a gas turbine engine - Google Patents
Sealing arrangement for a gas turbine engine Download PDFInfo
- Publication number
- US20110182721A1 US20110182721A1 US13/010,329 US201113010329A US2011182721A1 US 20110182721 A1 US20110182721 A1 US 20110182721A1 US 201113010329 A US201113010329 A US 201113010329A US 2011182721 A1 US2011182721 A1 US 2011182721A1
- Authority
- US
- United States
- Prior art keywords
- sealing arrangement
- arrangement according
- rotor
- vanes
- leaves
- 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.)
- Abandoned
Links
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C01—INORGANIC CHEMISTRY
- C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
- C01B21/00—Nitrogen; Compounds thereof
- C01B21/06—Binary compounds of nitrogen with metals, with silicon, or with boron, or with carbon, i.e. nitrides; Compounds of nitrogen with more than one metal, silicon or boron
- C01B21/068—Binary compounds of nitrogen with metals, with silicon, or with boron, or with carbon, i.e. nitrides; Compounds of nitrogen with more than one metal, silicon or boron with silicon
- C01B21/0682—Preparation by direct nitridation of silicon
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- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
- F16J15/3292—Lamellar structures
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/25—Manufacture essentially without removing material by forging
-
- 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
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- 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
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/57—Leaf seals
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a sealing arrangement between a stator assembly and a rotor 12 of a gas turbine engine, the rotor 12 being rotatable about an engine axis, the stator assembly comprising vanes 22 provided at their radially inner ends with a vane support structure 28 which comprises an annular platform 30 supporting the vanes and a radial flange 32 which extends radially inwardly from the platform, the sealing arrangement comprising an array of leaves 36 which extend inwardly from the radially inner periphery of the flange 32, towards a circumferential sealing surface 13 of the rotor 12.
Description
- The present invention relates to a sealing arrangement between a stator assembly and a rotor of a gas turbine engine, in particular, a sealing arrangement for sealing between compressor stator vanes and a compressor drum.
- Gas turbine engines include an axial flow compressor comprising a rotor in the form of a compressor drum located within a substantially annular casing. The compressor drum carries axially spaced sets of compressor blades, each set of compressor blades comprising a plurality of radially extending and circumferentially spaced rotor blades that rotate about the engine axis. A set of non-rotating stator vanes is positioned in each space between adjacent sets of compressor blades. Each set of stator vanes comprises a plurality of circumferentially spaced vanes that radially extend from the annular casing towards the compressor drum. It is necessary to seal between the radially inward end of each stator vane and the compressor drum in order to prevent high-pressure air from circulating beneath the vanes.
- In a known arrangement, for example as disclosed in GB 2426301, axially spaced and radially extending fins are provided on the compressor drum between adjacent sets of compressor blades. The stator vanes are provided with an abradable liner, which the fins rub against in use, thereby providing a seal between the stator vanes and the compressor drum. Whilst this arrangement is satisfactory, it does not allow for large relative radial movement between the compressor drum and the stator vanes and does not allow for differential thermal expansion of the components, whilst maintaining a good seal. For example, in an extreme event, the compressor drum rotates eccentrically with respect to the stator vanes, and the fins create a deep groove in the abradable liner. Subsequently, under normal running, the deep groove can provide a flow path beneath the vanes. This is undesirable.
- Further, machining the fins on the compressor drum can be complicated and time consuming and also the fins can serve as crack initiation points on the compressor drum. It is also necessary to replace the abradable liner periodically which results in an increased cost.
- It is therefore desirable to provide a sealing arrangement between stator vanes and a rotor which provides a good seal at all conditions.
- According to a first aspect of the present invention there is provided a sealing arrangement between a stator assembly and a rotor of a gas turbine engine, the rotor being rotatable about an engine axis, the stator assembly comprising vanes provided at their radially inner ends with a vane support structure which comprises an annular platform supporting the vanes and a radial flange which extends radially inwardly from the platform, the sealing arrangement comprising an array of leaves which extend inwardly from the radially inner periphery of the flange, towards a circumferential sealing surface of the rotor.
- The leaves may be directly attached to the radial flange. Alternatively, the leaves may be attached to a backing ring which is directly attached to the radial flange. A further possibility is for the leaves to be formed on the radial flange by a material removal operation such as machining or chemical etching, which removes the material between the leaves.
- The annular platform may comprise a plurality of circumferentially arranged openings, each opening having the end of a stator vane located within it. The end of each stator vane may be attached to the annular platform by upset forging.
- In a preferred arrangement the annular vane support structure comprises a plurality of circumferentially extending segments. Each segment may comprise a projection that cooperates with an adjacent segment to restrict relative axial movement between adjacent segments.
- The material of the rotor sealing surface may be hardened. For example, a hard coating may be applied to the rotor to form the sealing surface.
- The rotor may be a compressor drum or disc and the vanes may be compressor vanes.
- The invention also concerns a gas turbine engine comprising a sealing arrangement in accordance with any statement herein.
- The invention may comprise any combination of the features and/or limitations referred to herein, except combinations of such features as are mutually exclusive.
- Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings, in which:
-
FIG. 1 schematically shows a sectional view of part of a compressor section of a gas turbine engine; -
FIG. 2 schematically shows an enlarged view of a stator vane arrangement ofFIG. 1 ; -
FIG. 3 schematically shows the view A ofFIG. 2 ; -
FIG. 4 schematically shows a view of a stator vane, vane support and leaf seal; -
FIG. 5 schematically shows the view B ofFIG. 4 ; and -
FIG. 6 schematically shows the view C ofFIG. 4 . -
FIG. 1 shows acompressor section 10 of a gas turbine engine. Thecompressor section 10 comprises a rotor in the form of acompressor drum 12 having a plurality of axially spacedblade slots Compressor blades blade slots blades blades blade slots - The
compressor drum 12 is located within anouter casing 24 of the compressor. A plurality ofcompressor stator vanes 22 are attached to theouter casing 24 and are circumferentially arranged and extend towards thecompressor drum 12. Thestator vanes 22 are situated between the axially spaced sets ofblades inner ends 26 of thestator vanes 22 are attached to avane support structure 28 which is annular and extends around thecompressor drum 12. Aleaf seal 34 is disposed between thevane support 28 and theouter surface 13 of the compressor drum and provides a seal therebetween. Thisleaf seal 34 restricts the flow of high-pressure fluid underneath the radiallyinward ends 26 of thestator vanes 22. - With reference to
FIGS. 2 and 3 , thevane support 28 has a substantially L-shaped cross-section which comprises an annular axially extendingplatform 30 and a radially extendingflange 32 that extends from one axial end of theplatform 30 towards thecompressor drum 12. Theleaf seal 34 comprises a plurality of thin metal leaves 36 (or leaf seal elements) circumferentially arranged in an annular pack. In this embodiment, eachleaf 36 is welded at its radially outer edge directly to the inner periphery of the radially extendingflange 32 of thevane support 28. The plurality ofleaves 36 extend towards thecompressor drum 12 and a free end (the radially inward end) of eachleaf 36 contacts anouter sealing surface 13 of thecompressor drum 12. Theleaves 34 extend at an angle to the true radius and are resiliently deformable such that they can bend, or flex, along their length. For example, the leaves may be inclined in the operative direction of movement of the sealingsurface 13, in the radially inwards direction. The sealingsurface 13 of thecompressor drum 12 is constituted by ahard coating 15 in order to prevent theleaves 36 from abrading the surface during use. - In other embodiments, the
leaves 36 may be integrally formed with theflange 32 of thevane support structure 28 by either mechanical machining or chemical etching. Alternatively, theleaf seal 34 may be formed entirely separately from thevane support structure 28 by providing a backing ring (not shown) with a plurality ofleaves 36 extending from it. The backing ring may then be attached to the radially extendingflange 32 of thevane support structure 28 by welding, for example. Theleaf seal 34 may be formed as a continuous annular element, or more preferably, may be formed from a plurality of circumferentially extending leaf seal segments forming a continuous annulus. - In this embodiment the
vane support structure 28 is formed from a plurality of circumferentially extending segments. Thestator vanes 22 are individually cast and are attached at a radially outward end to theouter casing 24 and at a radiallyinner end 26 to the axially extendingplatform 30 of thevane support structure 28. The axially extendingplatform 30 is provided with an opening 41 for eachstator vane 22. The radiallyinward end 26 of eachstator vane 22 is located in a respective one of theopenings 41 and is attached to the axially extendingplatform 30 by hot upset forging. As will be readily apparent to one skilled in the art, thestator vanes 22 may be attached to thevane support 28 by any other suitable method. - Although it has been described that the
vane support structure 28 is formed from a plurality of circumferentially extending segments, in other embodiments thevane support structure 28 may be a continuous annular element. If thevane support structure 28 is formed from a plurality of circumferentially extending segments, the segments may be attached to one another by mechanical interlock, by welding, or by any other suitable method. -
FIGS. 4 , 5 and 6 show a second embodiment of the present invention that is similar to the embodiment ofFIGS. 1-3 . The radiallyinward ends 26 of a plurality ofstator vanes 22 are attached to avane support structure 28. The radiallyouter end 25 of eachstator vane 22 is provided with anattachment portion 27 for attaching thestator vane 22 to theouter casing 24 of the compressor. Thevane support structure 28 comprises an annular axially extendingplatform 30, to which the radiallyinward end 26 of eachstator vane 22 is attached, and aradially extending flange 32. Aleaf seal 34 is attached to the inner periphery of theradially extending portion 32. As in the first embodiment, theleaf seal 34 comprises a plurality ofleaves 36 welded at a first end to theradially extending flange 32. The leaves 36 extend at an angle to the true radius and are resiliently deformable such that they can bend, or flex, along their length. A free end (the radially inward end) of eachleaf 36 is in contact with the sealingsurface 13 of thecompressor drum 12 in use. - The
vane support structure 28 is a complete annulus that is formed from a plurality of circumferentially extending segments, each having a plurality ofstator vanes 22 attached thereto, The end of theradially extending flange 32 of eachvane support structure 28 segment is provided with two circumferentially extending projections located axially one on each side of theradially extending portion 32. As shown inFIG. 6 , theprojections radially extending flange 32 of an adjacent segment. This helps to restrict relative axial movement between adjacent segments and seals against axial leakage between adjacent vane radially extendingflanges 32. - In use, the
compressor drum 12 andcompressor blades stator vanes 22,vane support 28 andleaf seal 34. The free ends of theleaves 36 are in contact with the sealingsurface 13 of thecompressor drum 12. This restricts the flow of high-pressure fluid under the radially inward ends of thestator vanes 22 and therefore provides a good seal across each stage of the compressor. This in turn improves the efficiency of the gas turbine engine. The leaves 34 are in constant contact with the sealingsurface 13 of thecompressor drum 12. This ensures sealing at both transient and steady-state conditions. If there is radial displacement, or differential expansion under thermal or centrifugal effects, between thecompressor drum 12 and thecompressor stator vanes 22, then theleaf elements 36 can bend, or flex, along their length such that they are always in contact with the sealingsurface 13 of thecompressor drum 12. - The
vane support structure 28 andleaf seal 34 can be manufactured relatively easily and inexpensively when compared to prior art sealing arrangements that rely on fins provided on the compressor drum that abrade a liner provided on the stator vanes. - Although it has been described that the arrangement is for sealing between compressor stator vanes and a rotatable compressor drum, as will be readily apparent to one skilled in the art, the invention may be used to seal between any type of stator vane and rotor arrangement. Examples include, but are not limited to, fans and turbines.
Claims (12)
1. A sealing arrangement between a stator assembly and a rotor of a gas turbine engine, the rotor being rotatable about an engine axis, the stator assembly comprising vanes provided at their radially inner ends with a vane support structure which comprises an annular platform supporting the vanes and a radial flange which extends radially inwardly from the platform, the sealing arrangement comprising an array of leaves which extend inwardly from the radially inner periphery of the flange, towards a circumferential sealing surface of the rotor.
2. A sealing arrangement according to claim 1 , wherein the leaves are directly attached to the radial flange.
3. A sealing arrangement according to claim 1 , wherein the leaves are attached to a backing ring which is directly attached to the radial flange.
4. A sealing arrangement according to claim 1 , wherein the leaves are formed on the radial flange by a material removal operation.
5. A sealing arrangement according to claim 1 , wherein the annular platform comprises a plurality of circumferentially arranged openings, each opening having the end of a stator vane located within it.
6. A sealing arrangement according to claim 5 , wherein the end of each stator vane is attached to the annular platform by upset forging.
7. A sealing arrangement according to claim 1 , wherein the annular vane support structure comprises a plurality of circumferentially extending segments.
8. A sealing arrangement according to claim 7 , each segment comprises a projection that cooperates with an adjacent segment to restrict relative axial movement between adjacent segments.
9. A sealing arrangement according to claim 8 , wherein the projection is provided on the radial flange.
10. A sealing arrangement according to claim 1 , wherein the sealing surface is constituted by a hard coating on the rotor.
11. A sealing arrangement according to claim 1 , wherein the rotor is a compressor drum or disc and the vanes are compressor vanes.
12. A gas turbine engine comprising a sealing arrangement in accordance with claim 1 .
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1001072.6 | 2010-01-25 | ||
GBGB1001072.6A GB201001072D0 (en) | 2010-01-25 | 2010-01-25 | Sealing arrangemant foa a gas turbine engine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20110182721A1 true US20110182721A1 (en) | 2011-07-28 |
Family
ID=42045943
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/010,329 Abandoned US20110182721A1 (en) | 2010-01-25 | 2011-01-20 | Sealing arrangement for a gas turbine engine |
Country Status (3)
Country | Link |
---|---|
US (1) | US20110182721A1 (en) |
EP (1) | EP2348194A3 (en) |
GB (1) | GB201001072D0 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130183145A1 (en) * | 2012-01-17 | 2013-07-18 | Joseph T. Caprario | Hybrid inner air seal for gas turbine engines |
US20160123170A1 (en) * | 2014-10-30 | 2016-05-05 | United Technologies Corporation | Sealing systems |
US10544699B2 (en) * | 2017-12-19 | 2020-01-28 | Rolls-Royce Corporation | System and method for minimizing the turbine blade to vane platform overlap gap |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012006710A1 (en) | 2012-01-18 | 2013-07-18 | Ihi Charging Systems International Gmbh | Supercharger for internal combustion engine i.e. reciprocating internal combustion engine, has supporting element fastened at bearing housing by attachment element that is partially held in housing that includes turbine |
DE102012001238A1 (en) | 2012-01-18 | 2013-07-18 | Ihi Charging Systems International Gmbh | Supercharger for lifting cylinder internal combustion engine of passenger car, has lid element partially fastened at housing of radial-flow turbine by rigid attachment elements that are retained in lid element and in turbine housing |
US20130315708A1 (en) * | 2012-05-25 | 2013-11-28 | Jacob Romeo Rendon | Nozzle with Extended Tab |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3917150A (en) * | 1973-11-23 | 1975-11-04 | Rolls Royce 1971 Ltd | Seals and method of manufacture thereof |
US5181728A (en) * | 1991-09-23 | 1993-01-26 | General Electric Company | Trenched brush seal |
US6343792B1 (en) * | 1998-07-13 | 2002-02-05 | Mitsubishi Heavy Industries, Ltd. | Shaft seal and turbine using the same |
US20030062685A1 (en) * | 2001-09-28 | 2003-04-03 | Eagle Industry Co., Ltd | Brush seal and brush seal device |
US6543995B1 (en) * | 1999-08-09 | 2003-04-08 | United Technologies Corporation | Stator vane and stator assembly for a rotary machine |
US6736597B2 (en) * | 2001-10-09 | 2004-05-18 | Mitsubishi Heavy Industries, Ltd. | Axis seal mechanism and turbine |
US20060024156A1 (en) * | 2004-07-29 | 2006-02-02 | Alstom Technology Ltd | Axial flow steam turbine assembly |
US20080061513A1 (en) * | 2006-09-12 | 2008-03-13 | General Electric Company, | Shaft seal using shingle members |
US7695244B2 (en) * | 2005-01-28 | 2010-04-13 | Rolls-Royce Plc | Vane for a gas turbine engine |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2426301B (en) | 2005-05-19 | 2007-07-18 | Rolls Royce Plc | A seal arrangement |
US20080050222A1 (en) * | 2006-08-23 | 2008-02-28 | General Electric Company | Singlet welded nozzle hybrid design for a turbine |
-
2010
- 2010-01-25 GB GBGB1001072.6A patent/GB201001072D0/en not_active Ceased
-
2011
- 2011-01-20 EP EP11151498.0A patent/EP2348194A3/en not_active Withdrawn
- 2011-01-20 US US13/010,329 patent/US20110182721A1/en not_active Abandoned
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3917150A (en) * | 1973-11-23 | 1975-11-04 | Rolls Royce 1971 Ltd | Seals and method of manufacture thereof |
US5181728A (en) * | 1991-09-23 | 1993-01-26 | General Electric Company | Trenched brush seal |
US6343792B1 (en) * | 1998-07-13 | 2002-02-05 | Mitsubishi Heavy Industries, Ltd. | Shaft seal and turbine using the same |
US6543995B1 (en) * | 1999-08-09 | 2003-04-08 | United Technologies Corporation | Stator vane and stator assembly for a rotary machine |
US20030062685A1 (en) * | 2001-09-28 | 2003-04-03 | Eagle Industry Co., Ltd | Brush seal and brush seal device |
US6736597B2 (en) * | 2001-10-09 | 2004-05-18 | Mitsubishi Heavy Industries, Ltd. | Axis seal mechanism and turbine |
US20060024156A1 (en) * | 2004-07-29 | 2006-02-02 | Alstom Technology Ltd | Axial flow steam turbine assembly |
US7695244B2 (en) * | 2005-01-28 | 2010-04-13 | Rolls-Royce Plc | Vane for a gas turbine engine |
US20080061513A1 (en) * | 2006-09-12 | 2008-03-13 | General Electric Company, | Shaft seal using shingle members |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130183145A1 (en) * | 2012-01-17 | 2013-07-18 | Joseph T. Caprario | Hybrid inner air seal for gas turbine engines |
US9416673B2 (en) * | 2012-01-17 | 2016-08-16 | United Technologies Corporation | Hybrid inner air seal for gas turbine engines |
US20160123170A1 (en) * | 2014-10-30 | 2016-05-05 | United Technologies Corporation | Sealing systems |
US10280780B2 (en) * | 2014-10-30 | 2019-05-07 | United Technologies Corporation | Sealing systems for gas turbine engine vane platforms |
US10544699B2 (en) * | 2017-12-19 | 2020-01-28 | Rolls-Royce Corporation | System and method for minimizing the turbine blade to vane platform overlap gap |
Also Published As
Publication number | Publication date |
---|---|
EP2348194A2 (en) | 2011-07-27 |
EP2348194A3 (en) | 2013-05-22 |
GB201001072D0 (en) | 2010-03-10 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: ROLLS-ROYCE PLC, GREAT BRITAIN Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SAUNDERS, DUNCAN;REEL/FRAME:025670/0621 Effective date: 20101112 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |