US20080095616A1 - Fluid brush seal with segment seal land - Google Patents
Fluid brush seal with segment seal land Download PDFInfo
- Publication number
- US20080095616A1 US20080095616A1 US11/584,062 US58406206A US2008095616A1 US 20080095616 A1 US20080095616 A1 US 20080095616A1 US 58406206 A US58406206 A US 58406206A US 2008095616 A1 US2008095616 A1 US 2008095616A1
- Authority
- US
- United States
- Prior art keywords
- disk
- land
- seal
- blade
- rotor
- 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
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Images
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
- F01D11/001—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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F05D2240/56—Brush seals
Abstract
A turbine rotor for a turbine engine includes multiple rotor disks having rotor blades mounted about the circumference of each of the rotor disks. A fluid seal extends about the circumference of each rotor disk in close proximity to a stationary component of the rotor to separate the space between the rotor blades and a stationary component into separate cavities. The fluid seal includes a seal land on the rotor disk and a brush seal extending from the stationary component. A plurality of disk land segments and a plurality of blade land segments form the seal land. The disk seal segments are located on the rotor disk between the rotor blades. The blade land segments are located on the rotor blades. After the rotor blades are assembled, the blade land segments and the disk land segments fit together to form a segmented ring-like seal land around the circumference of the rotor disk.
Description
- This application discloses subject matter related to co-pending US patent applications “HAMMERHEAD FLUID SEAL” (U.S. patent application Ser. No. 11/146,801), “COMBINED BLADE ATTACHMENT AND DISK LUG FLUID SEAL” (U.S. patent application Ser. No. 11/146,798) and “BLADE NECK FLUID SEAL” (U.S. patent application No. 11/146,660), each filed on Jul. 7, 2005, and “INTEGRATED BLADED FLUID SEAL” (U.S. patent application Ser. No. 11/260,357) filed on Oct. 27, 2005.
- The invention generally relates to an arrangement for fluid seals within a gas turbine engine.
- Turbine engines include high and low pressure rotor spools comprising multiple rotor disks. Fluid seals are formed integrally into each rotor disk to contact stator components, such as a tangential on-board injector. The seals restrict leakage of compressed air from between the stator component and the rotor disks and separate the lower pressure gaspath air from high pressure air used for cooling.
- Due to the rotor disk geometry, multiple machining passes are required to produce the thin sectional area required for the fluid seal. This is unduly complex. Also, during operation of the engine, the fluid seal may contact an abradable material on the stationary components, causing wear. Because the fluid seal is integrally formed with the rotor disk of the compressor, the entire rotor disk must be repaired or replaced when the fluid seal has worn.
- An improved arrangement for sealing fluids within a gas turbine engine is needed.
- An example turbine engine rotor according to this invention includes an arrangement for incorporating a fluid seal assembly while reducing wear on the rotor disk.
- A typical turbine engine rotor includes multiple rotor disks with rotor blades mounted about the circumference of each of the rotor disks. A plurality of stator vanes extend axially between adjacent rotor disks. A fluid seal assembly extends about the circumference of each rotor disk in close proximity to a stationary component of the compressor. The fluid seal assembly separates the space between the rotor blades and stationary components into separate pressurized cavities.
- The fluid seal includes a seal land in contact with a brush seal. The seal land extends about the circumference of the disk rim and includes a plurality of disk land segments and a plurality of blade land segments fitting together to form a segmented seal land. The disk land segments are integrally formed with the rotor disk between the rotor blades. The blade land segments are integrally formed with the rotor blades. When the rotor blades are assembled to the rotor disk, the blade land segments and the disk land segments fit together to form a segmented, ring-like seal land around the circumference of the rotor disk.
- Each disk land segment has a first interlocking feature interfitting with a second interlocking feature on the blade land segments to align the land segments and reduce circumferential and radial fluid leaks.
- These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
-
FIG. 1 is a schematic view of an example turbine engine of the present invention; -
FIG. 2 illustrates a portion of a cross-section of a typical rotor for the example turbine engine of the present invention; -
FIG. 3 is an enlarged view of region 3-3 fromFIG. 2 , illustrating a portion of an example fluid seal; -
FIG. 4 is a perspective view of an example disk land segment and blade land segment of the present invention prior to assembly; -
FIG. 5 illustrates a portion of a cross-section of another example turbine rotor of the present invention; -
FIG. 6 is an enlarged view of region 6-6 fromFIG. 5 , illustrating a portion of another example fluid seal; and -
FIG. 7 is a perspective view of another example disk land segment and blade land segment of the present invention prior to assembly. -
FIG. 1 is a schematic view of aturbine engine 10. Air is pulled into theturbine engine 10 by afan 12 and flows through alow pressure compressor 14 and ahigh pressure compressor 16. Fuel is mixed with the air, and combustion occurs within thecombustor 18. Exhaust from combustion flows through ahigh pressure turbine 20 and alow pressure turbine 22 prior to leaving the engine through anexhaust nozzle 24. -
FIG. 2 illustrates a portion of a cross-section of a typical turbine engine turbine, showing arotor disk 26, which is one of several defining a rotor. Eachrotor disk 26 rotates about an axis A located along the longitudinal centerline of theturbine engine 10. A plurality ofrotor blades 28 are mounted about the circumference of eachrotor disk 26. A plurality of stator vanes 30 extend between therotor blades 28 of axiallyadjacent rotor disks 26, as shown. - Each
rotor disk 26 includes adisk rim 32. Thedisk rim 32 secures therotor blades 28. Afluid seal 34 is located between therotor disk 26 and a stationary part of the turbine, such as a stator vane, a support or a tangential on-board injector (TOBI) 36. Thefluid seal 34 defines acavity 38 located axially above thefluid seal 34 and further defined by thestator vane 30 and therotor blade 28. Air within thecavity 38 is flowing circumferentially about the axis A of rotation for therotor disk 26. Aninterior cavity 40 is located axially below thefluid seal 34 and defined by therotor disk 26 and thestationary component 36. Anozzle 42 leading from the TOBI 36 allows high pressure cooling air to reach theinterior cavity 40 to cool therotor disk 26. -
FIG. 3 illustrates an enlarged view of theexample fluid seal 34. Thefluid seal 34 includes a segmentedseal land 44 and abrush seal 46. Theseal land 44 extends about the circumference of thedisk rim 32. Theseal land 44 is preferably formed of the same material as therotor disk 26, such as any ferrous, nickel, or ceramic materials. Theseal land 44 may also be coated with a wear resistant hard facing or coating to reduce wear. - The
seal land 44 is in contact with thebrush seal 46 extending from thestationary component 36. Theseal land 44 is illustrated as extending axially toward thestationary component 36 along the axis A of theturbine engine 10. However, theseal land 44 can extend toward any stationary component of theturbine engine 10. Thebrush seal 46 includes anaxial locking feature 48 to retain thebrush seal 46 to thestationary component 36 and to prevent axial movement of thebrush seal 46 along the axis A of theturbine engine 10. Thebrush seal 46 extends in a radially inward direction from thestationary component 36 and hasbristles 50 which contact aradial face 52 of theseal land 44. Thebristles 50 are wire bristles or the like to provide radial resilience and reduce wear on theseal land 44. - Referring to
FIG. 4 , the segmentedseal land 44 includes a plurality ofdisk land segments 54 and a plurality ofblade land segments 56. Spaced around the circumference of thedisk rim 32,segments disk rim 32. Thedisk land segments 54 are integrally formed in thedisk rim 32 between therotor blades 28. - The
blade land segments 56 are integrally formed with therotor blades 28. Therotor blade 28 has aroot 57 contoured to fit into a complimentary contouredblade slot 58 in thedisk rim 32.Walls 59 in thedisk rim 32 define theindividual blade slots 58. Therotor blade 28 is loaded in theblade slot 58, and eachdisk land segment 54 andblade land segment 56 mate with a circumferentiallyadjacent land segment blade land segments 56 are worn, theindividual rotor blades 28 andblade land segments 56 can be repaired or replaced. Also, use of thebrush seal 46 reduces wear on theseal land 44, extending the life of thefluid seal 34 compared to the prior art abradable material. - After the
rotor blade 28 is assembled in theblade slot 58, thedisk land segments 54 and theblade land segments 56 fit together to form a segmented, ring-like fluid seal 34 around the circumference of therotor disk 26. Eachdisk land segment 54 has afirst interlocking feature 60, and eachblade land segment 56 has asecond interlocking feature 62. Thefirst interlocking feature 60 and thesecond interlocking feature 62 interfit to align thedisk land segments 54, with theblade land segments 56. In the example shown, thefirst interlocking feature 60 is a protrusion extending from thedisk land segment 54, and thesecond interlocking feature 62 is a protrusion extending from theblade land segment 56. The protrusions overlap one another to create a shiplap joint and reduce circumferential and radial fluid leaks between thedisk land segments 54 and theblade land segments 56. Alternatively, thefirst interlocking feature 60 and the second interlocking feature can be tongue and groove or other interfitting elements. -
FIG. 5 illustrates a portion of a cross-section of another example embodiment of a turbine including arotor disk 26 defining a turbine rotor. Afluid seal 102 is located between therotor disk 26 and astationary component 36. Thefluid seal 102 defines acavity 38 located axially above thefluid seal 102 and further defined by thestator vane 30 and therotor blade 28. Aninterior cavity 40 is located axially below thefluid seal 102 and defined by therotor disk 26 and thestationary component 36. Anozzle 42 leading from thestationary component 36 allows high pressure cooling air to reach theinterior cavity 40 to cool therotor disk 26. -
FIG. 6 illustrates an enlarged view of theexample fluid seal 102. Thefluid seal 102 includes aseal land 104 and abrush seal 106. Theseal land 104 extends about the circumference of thedisk rim 32. Theseal land 104 is preferably formed of the same material as therotor disk 26, such as any ferrous or nickel materials. Theseal land 104 may also be coated with a wear resistant hard facing or coating to reduce wear. - The
seal land 104 is in contact with thebrush seal 106 extending axially from thestationary component 36. Theseal land 104 is illustrated as extending axially toward thestationary component 36 along the axis A of theturbine engine 10. Thebrush seal 106 includes anaxial locking feature 108 to retain thebrush seal 106 to thestationary component 36 and to prevent axial movement of thebrush seal 106 along the axis A of theturbine engine 10. Thebrush seal 106 extends in an axial direction from thestationary component 36 and hasbristles 110 which contact aradial face 112 of theseal land 104. Thebristles 110 are wire bristles or the like to provide radial resilience and to reduce wear on theseal land 104. - Referring to
FIG. 7 , theseal land 104 includes a plurality of disk land segments 114 and a plurality ofblade land segments 116 spaced around the circumference of thedisk rim 32 and fitting together to form asolid seal land 104 about thedisk rim 32. The disk land segments 114 are integrally formed in thedisk rim 32 between therotor blades 28. - The
blade land segments 116 are integrally formed in therotor blades 28. Therotor blade 28 is loaded into ablade slot 58 in thedisk rim 32.Walls 59 in thedisk rim 32 define theindividual blade slots 58. When therotor blade 28 is loaded in theblade slot 58, each disk land segment 114 andblade land segment 116 mate with a circumferentiallyadjacent land segment 114 or 116 to provide a rigid structure. When theblade land segments 116 are worn, theindividual rotor blades 28 andblade land segments 116 can be repaired or replaced. Thebrush seal 106 reduces wear on theseal land 104 extending the life of thefluid seal 102. - After the
rotor blade 28 is assembled in theblade slot 58, the disk land segments 114 and theblade land segments 116 fit together to form a segmented, ring-like fluid seal 34 around the circumference of therotor disk 26. Each disk land segment 114 can have afirst interlocking feature 60, and eachblade land segment 116 can have asecond interlocking feature 62 as illustrated inFIG. 4 of the previous example. The first interlocking feature and the second interlocking feature interfit to align the disk land segments 114 with theblade land segments 116. The first interlocking feature and the second interlocking feature can be a ship lap, a tongue and a groove or other interfitting elements. - Although the example embodiment discloses an arrangement of assembling fluid seal segments onto a rotor disk for a turbine, the arrangement may be used for any rotor and seal assembly.
- Although a preferred embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Claims (17)
1. A turbine engine comprising:
a rotor disk to rotate about an axis defining a disk rim and having a plurality of rotor blades mounted to the disk rim;
a plurality of disk land segments extending from the disk rim between each of the plurality of rotor blades;
a plurality of blade land segments extending from each of the plurality of rotor blades, wherein the plurality of disk land segments and the plurality of blade land segments form a seal land located about a circumference of the disk rim; and
a brush seal extending from a stationary component of the turbine engine and contacting the seal land.
2. The turbine engine of claim 1 , wherein the plurality of disk land segments are integrally formed in the rotor disk.
3. The turbine engine of claim 1 , wherein the plurality of blade land segments are integrally formed in each of the plurality of rotor blades.
4. The turbine engine of claim 1 , wherein the seal land comprises a radial face and the brush seal extends axially to contact the radial face.
5. The turbine engine of claim 1 , wherein the seal land comprises an axial face and the brush seal extends radially inward to contact the axial face.
6. The turbine engine of claim 1 , wherein the stationary component is a tangential on-board injector.
7. The turbine engine of claim 1 , wherein the brush seal further comprises an axial locking feature to prevent axial movement of the brush seal.
8. The turbine engine of claim 1 , wherein an interfitting structure on each of the plurality of disk land segments and the plurality of blade land segments align the plurality of disk land segments and the plurality of blade land segments.
9. A fluid seal assembly for a jet engine comprising:
a plurality of rotor disks rotating about an axis and each defining a disk rim and having a plurality of rotor blades mounted to the disk rim;
a plurality of disk land segments extending from the disk rim between each of the plurality of rotor blades;
a plurality of blade land segments extending from each of the plurality of rotor blades, wherein the plurality of disk land segments and the plurality of blade land segments form a seal land located about the circumference of the disk rim; and
a brush seal extending from a stationary component of the turbine engine to contact the seal land.
10. The fluid seal assembly of claim 9 , wherein the plurality of disk land segments are integrally formed with the rotor disk.
11. The fluid seal assembly of claim 9 , wherein the plurality of blade land segments are integrally formed with each of the plurality of rotor blades.
12. The fluid seal assembly of claim 9 , wherein the seal land comprises a radial face and the brush seal extends axially to contact the radial face.
13. The fluid seal assembly of claim 9 , wherein the seal land comprises an axial face and the brush seal extends in a radial inward direction to contact the axial face.
14. The fluid seal assembly of claim 9 , wherein the brush seal further comprises an axial locking feature to prevent axial movement of the brush seal.
15. The fluid seal assembly of claim 9 , the wherein interfitting structure on each of the plurality of disk land segments and the plurality of blade land segments align the plurality of disk land segments and the plurality of blade land segments.
16. A rotor blade comprising:
a blade platform having a blade root extending from the blade platform for receiving in a blade slot of a rotor disk; and
a blade seal segment extending from the blade root, wherein the blade seal segment defines a seal land for contacting a brush seal extending from a stationary turbine engine component.
17. The rotor blade of claim 16 , comprising a first interlocking feature on the blade seal segment for interfitting with a second interlocking feature on a disk seal segment of the rotor disk.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/584,062 US20080095616A1 (en) | 2006-10-20 | 2006-10-20 | Fluid brush seal with segment seal land |
EP07254135.2A EP1918523B1 (en) | 2006-10-20 | 2007-10-18 | Rotor blade and corresponding turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/584,062 US20080095616A1 (en) | 2006-10-20 | 2006-10-20 | Fluid brush seal with segment seal land |
Publications (1)
Publication Number | Publication Date |
---|---|
US20080095616A1 true US20080095616A1 (en) | 2008-04-24 |
Family
ID=38710451
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/584,062 Abandoned US20080095616A1 (en) | 2006-10-20 | 2006-10-20 | Fluid brush seal with segment seal land |
Country Status (2)
Country | Link |
---|---|
US (1) | US20080095616A1 (en) |
EP (1) | EP1918523B1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8794918B2 (en) | 2011-01-07 | 2014-08-05 | General Electric Company | System for adjusting brush seal segments in turbomachine |
US9121297B2 (en) | 2011-03-28 | 2015-09-01 | General Electric Company | Rotating brush seal |
US9255486B2 (en) | 2011-03-28 | 2016-02-09 | General Electric Company | Rotating brush seal |
US10458266B2 (en) | 2017-04-18 | 2019-10-29 | United Technologies Corporation | Forward facing tangential onboard injectors for gas turbine engines |
USD873981S1 (en) * | 2017-06-27 | 2020-01-28 | Nok Corporation | Seal ring |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011083814A1 (en) | 2011-09-30 | 2013-04-04 | Mtu Aero Engines Gmbh | Segmented component |
FR2988129B1 (en) * | 2012-03-15 | 2015-12-25 | Snecma | SEALING SYSTEM FOR A DISTRIBUTOR OF A CORRESPONDING TURBOMACHINE, TURBINE AND TURBOMACHINE TURBINE. |
US9097129B2 (en) * | 2012-05-31 | 2015-08-04 | United Technologies Corporation | Segmented seal with ship lap ends |
AT13415U1 (en) * | 2012-12-11 | 2013-12-15 | Mtu Aero Engines Gmbh | Sealing element with brushes and hooks |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4218189A (en) * | 1977-08-09 | 1980-08-19 | Rolls-Royce Limited | Sealing means for bladed rotor for a gas turbine engine |
US4685863A (en) * | 1979-06-27 | 1987-08-11 | United Technologies Corporation | Turbine rotor assembly |
US4701105A (en) * | 1986-03-10 | 1987-10-20 | United Technologies Corporation | Anti-rotation feature for a turbine rotor faceplate |
US5310319A (en) * | 1993-01-12 | 1994-05-10 | United Technologies Corporation | Free standing turbine disk sideplate assembly |
US5328328A (en) * | 1992-05-27 | 1994-07-12 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Sealing device between blade stages and a rotary drum, particularly for preventing leaks around the stages of straightener blades |
US5522698A (en) * | 1994-04-29 | 1996-06-04 | United Technologies Corporation | Brush seal support and vane assembly windage cover |
US5622698A (en) * | 1990-06-08 | 1997-04-22 | Miami University | Method and composition for increasing the supercooling point in invertebrates |
US7121791B2 (en) * | 2003-04-25 | 2006-10-17 | Rolls-Royce Deutschland Ltd & Co Kg | Main gas duct internal seal of a high-pressure turbine |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1450553A (en) * | 1973-11-23 | 1976-09-22 | Rolls Royce | Seals and a method of manufacture thereof |
US6619030B1 (en) * | 2002-03-01 | 2003-09-16 | General Electric Company | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors |
-
2006
- 2006-10-20 US US11/584,062 patent/US20080095616A1/en not_active Abandoned
-
2007
- 2007-10-18 EP EP07254135.2A patent/EP1918523B1/en not_active Expired - Fee Related
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4218189A (en) * | 1977-08-09 | 1980-08-19 | Rolls-Royce Limited | Sealing means for bladed rotor for a gas turbine engine |
US4685863A (en) * | 1979-06-27 | 1987-08-11 | United Technologies Corporation | Turbine rotor assembly |
US4701105A (en) * | 1986-03-10 | 1987-10-20 | United Technologies Corporation | Anti-rotation feature for a turbine rotor faceplate |
US5622698A (en) * | 1990-06-08 | 1997-04-22 | Miami University | Method and composition for increasing the supercooling point in invertebrates |
US5328328A (en) * | 1992-05-27 | 1994-07-12 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Sealing device between blade stages and a rotary drum, particularly for preventing leaks around the stages of straightener blades |
US5310319A (en) * | 1993-01-12 | 1994-05-10 | United Technologies Corporation | Free standing turbine disk sideplate assembly |
US5522698A (en) * | 1994-04-29 | 1996-06-04 | United Technologies Corporation | Brush seal support and vane assembly windage cover |
US7121791B2 (en) * | 2003-04-25 | 2006-10-17 | Rolls-Royce Deutschland Ltd & Co Kg | Main gas duct internal seal of a high-pressure turbine |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8794918B2 (en) | 2011-01-07 | 2014-08-05 | General Electric Company | System for adjusting brush seal segments in turbomachine |
US9121297B2 (en) | 2011-03-28 | 2015-09-01 | General Electric Company | Rotating brush seal |
US9255486B2 (en) | 2011-03-28 | 2016-02-09 | General Electric Company | Rotating brush seal |
US10458266B2 (en) | 2017-04-18 | 2019-10-29 | United Technologies Corporation | Forward facing tangential onboard injectors for gas turbine engines |
USD873981S1 (en) * | 2017-06-27 | 2020-01-28 | Nok Corporation | Seal ring |
Also Published As
Publication number | Publication date |
---|---|
EP1918523A2 (en) | 2008-05-07 |
EP1918523A3 (en) | 2011-02-23 |
EP1918523B1 (en) | 2019-07-24 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ALVANOS, IOANNIS;VIRTUE, JR., JOHN P.;REEL/FRAME:018726/0799 Effective date: 20061018 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |