US20140301851A1 - Rotor - Google Patents
Rotor Download PDFInfo
- Publication number
- US20140301851A1 US20140301851A1 US14/245,320 US201414245320A US2014301851A1 US 20140301851 A1 US20140301851 A1 US 20140301851A1 US 201414245320 A US201414245320 A US 201414245320A US 2014301851 A1 US2014301851 A1 US 2014301851A1
- Authority
- US
- United States
- Prior art keywords
- rotor
- rotor disc
- disc
- discs
- interrupted screw
- 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
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
- F05D2230/60—Assembly methods
-
- 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
- F05D2230/60—Assembly methods
- F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- This application claims priority to European application 13162666.5 filed Apr. 8, 2013, the contents of which are hereby incorporated in its entirety.
- The present invention relates to a rotor, for example for a gas-turbine engine. More particularly, the present invention also relates to mechanical coupling between the rotor discs of the rotor.
- State-of-the-art gas-turbines engines typically comprise three sections: A compressor, a combustor, and a turbine. Before entering the combustor, pressure of the working medium, typically air, is increased to approximately by the compression section. The compressed air then leaves the compression section and enters the combustor, where it is mixed with fuel and the combustion process takes place. After combustion, hot air leaves the combustor and is fed into the turbine.
- A gas-turbine engine comprises a rotor. The rotor can be assembled from discs in a stack-up operation where components such as the compressor discs and the turbine discs are connected coaxially together along the axis of rotation. Various ways of connecting the discs of a rotor have been put forward. U.S. Pat. No. 3,976,399 discloses rotor discs stacked on a central connecting rod. The rotor discs of U.S. Pat. No. 3,976,399 are held in place by half-shells which are clamped together by clamping rings. U.S. Pat. No. 3,976,399 also discloses heat-shrinking rotors discs onto a central connecting rod. U.S. Pat. No. 7,384,075 discloses threaded joints between the components of a rotor. The threaded joint is additionally secured by an anti-rotation locking mechanism. U.S. Pat. No. 5,537,814 and U.S. Pat. No. 8,100,666 disclose a clamping nut and a tie shaft to axially clamp a turbine disc together with other rotor components. U.S. Pat. No. 4,310,286 discloses bolted joints to fixate the discs of a rotor.
- The mechanical connections between the rotor discs of a gas-turbine engine have to meet a number of conflicting technical requirements: The rotor of a gas-turbine engine may deflect, so the axis of rotation and the center of mass of the rotor will no longer coincide. The connections between the rotors discs of a gas-turbine engine shall thus be torsionally stiff. The connections between the rotor discs of a gas-turbine engine shall be designed for a critical speed of the rotor well above the operational speed of 1500 or 15000 rpm.
- The pressures inside the gas-turbine engine may be severe. The rotor of a gas-turbine engine shall be designed to withstand the corresponding stresses.
- The new stack of rotor discs shall minimize the effort involved in its fabrication. In particular, the fabrication of the stack of rotor discs shall minimize the use of special tools.
- Despite the aforementioned requirement of torsional stiffness, the joints between rotor discs shall allow easy and effortless removal and replacement of discs when the rotor is in stationary position. In other words, any rotor discs shall be easily displaceable during maintenance or repair.
- The present application is oriented towards providing the aforementioned needs and towards overcoming the aforementioned difficulties.
- The present disclosure is about improved mechanical connections between the discs of a rotor. In order to arrive at a connection that is torsionally stiff and leakage-proof, an interrupted screw on each side of a reciprocally connected rotor disc is proposed. An interrupted screw is a screw whose surface is divided longitudinally into several blank or cutaway sections. The two rotor discs are locked together by a fraction of a turn.
- After connecting the two rotor discs, the surfaces of the interrupted screw of the first rotor disc and of the reciprocally made nut of the second rotor disc align. The alignment of the two surfaces results in a connection that is torsionally stiff and allows for a critical speed of the rotor well above 1500 to 15000 rpm.
- The interrupted screw on each side of the reciprocally connected rotor discs can be made of the same metals. That way, corrosion issues due to the use of dissimilar metals are eliminated.
- The rotor discs can also be made of different metals, in particular of different steel alloys. A gas-turbine engine may require different alloys to be used for the rotor discs of the compressor and for the rotor discs of the combustor. The present disclosure allows rotor discs made of different metals or alloys to be connected.
- To assemble a rotor, the two or more rotor discs are engaged and one rotor disc is rotated by a fraction of a turn against the other rotor disc. The rotation is carried out about the axis of rotation common to the two rotor discs. That axis will later become the axis of rotation of the rotor. As soon as the two discs are connected, yet another rotor disc is connected the stack of previously joined rotor discs by engaging said disc and the stack of rotor discs. The process continues until the assembly of the rotor is complete.
- Likewise, during repair or maintenance of a rotor, a disc is removed from the stack of rotor discs by rotating it by a fraction of a turn. The direction of the rotation is now opposite to the direction when two discs were connected. The disc can then be removed from the remaining stack rotor discs. The process may continue until the stack of rotor discs has been completely disassembled.
- The foregoing objects and many of the attendant advantages of this invention will become more readily appreciated as the same becomes better understood by reference to the following detailed description when taken in conjunction with the accompanying drawings, wherein:
-
FIG. 1 is a cut-away view of a rotor disc according to the application. -
FIG. 2 is a three-dimensional view of one side of said rotor disc. -
FIG. 3 is a front view of the other side of said rotor disc. -
FIG. 4 is a three-dimensional view of two rotor discs before being connected. -
FIG. 5 is a three-dimensional view of a stack of rotor discs. -
FIG. 6 gives a three-dimensional view of a rotor disc according to another embodiment of the invention. -
FIG. 7 is a three-dimensional view of the rotor disc ofFIG. 6 from the other side. -
FIG. 8 is a three-dimensional view of connected rotor discs as perFIG. 6 andFIG. 7 . -
FIG. 1 gives a cut-away view of arotor disc 1 according to the application Therotor disc 1 comprises a plurality of protrusions arranged along the outer circumference of the rim 3. On each of itssides rotor disc 1 provides an interrupted screw. The two interrupted screws on eachside side 4 of arotor disc 1 may cooperate with the interrupted screw on theopposite side 5 of another rotor disc.FIG. 1 shows the interrupted screw on oneside 5 of the rotor disc comprises a plurality ofslots rotor disc 1, so the distance between each pair of adjacent slots is the same. Theslots surfaces 7 arranged in between theslots slots support portions 8. Thesupport portions 8 carry the mechanical forces applied to theslots support portions 8 of eachslot - On the
other side 4 of therotor disc 1,segments side 4 of therotor disc 1 reciprocates with a slot on theother side 5 of thedisc 1. In a preferred embodiment, thesegments slots other side 5 of therotor disc 1. - The
segments slots segments slot slots segments segments segments segments slots - In another embodiment, the
disc 1 with theslots segments slots disc 1 with theslots surface 7 increases. Thesegments slots slots segments segments slots rotor disc 1 rotates as part of a rotor. In other words, heat treatment will not only result in torsional stiffness but also in compensation of centrifugal forces when the rotor is in service. - It should be mentioned the clamping surfaces 7 of the
slots FIG. 1 point outwards from the axis of rotation of thedisc 1. In another embodiment, the clamping surfaces 7 of theslots segments -
FIG. 2 provides a three-dimensional view of arotor disc 1 according to the application. This three-dimensional drawing shows therotor disc 1 ofFIG. 1 viewed from one of itssides 4.FIG. 2 shows a total of sixsegments rotor disc 1 would be 60° . Also, thesegments FIG. 2 have got the shape of bent cylinders. In other embodiments, the cross-sections ofsegments -
FIG. 3 shows a front view of therotor disc 1 ofFIG. 1 .FIG. 3 shows therotor disc 1 ofFIG. 1 as viewed from itsother side 5.FIG. 3 shows a total of sixslots rotor disc 1. Theslots segments other side 4 of an adjacent rotor disc. -
FIG. 4 shows a pair ofrotor discs rotor discs FIGS. 1-3 . Thefirst rotor disc 1 a provides an arrangement ofslots segments second rotor disc 1 b. In order to connect the tworotor discs discs FIG. 4 , one disc would be rotated by 60° against the other disc because there is a total sixsegments slots - The clamping surfaces 7 of the
slots segments discs discs - To disconnect the two
discs disc 1 a with theslots other disc 1 b. The twodiscs slots segments heating disc 1 a faster than theother disc 1 b. Therotor discs rotor discs - While
FIG. 4 shows a pair of rotor discs before being joined,FIG. 5 shows a stack of fiverotor discs FIG. 5 it is possible to connect a plurality of rotor discs with reciprocating interrupted screws on either side. The resulting stack of connected rotor discs will form a rotor that is torsionally stiff and whose critical speed is well beyond 1500 to 15000 rpm. -
FIG. 5 also indicates the stack of rotor discs provides an aperture along the common central axis of the rotor discs. The aperture common to all rotor discs allows other elements such as shafts to be arranged inside the aperture. There is thus sufficient space inside stack of rotor discs to arrange separate shafts for the compressor and for the turbine sections of a gas-turbine engine. - The
rotor discs FIG. 5 have all got the same diameters. In another embodiment, rotor discs as per this application are connected where the rotor discs differ in diameter. -
FIG. 6 shows arotor disc 1 according to another embodiment of the application. Therotor disc 1 ofFIG. 6 comprises a protrudingrim 10. Therim 10 provides a plurality ofwedges wedges outer rim 10. The presentFIG. 6 shows a total of eight wedges. Therim 10 and thewedges slots FIG. 3 . -
FIG. 7 shows arotor disc 1 with an interrupted screw that reciprocates the interrupted screw shown onFIG. 6 . Therotor disc 1 provides agroove 12 with a plurality ofwedges segments FIG. 2 . In a preferred embodiment, thewedges rim 10 and thewedges groove 12 are made of the same materials. Different materials are also possible. - In order to connect the rotor discs shown on
FIG. 6 and onFIG. 7 , the protrudingrim 10 ofFIG. 6 is introduced into thegroove 12 shown onFIG. 7 . One of the discs is then rotated by a fraction of a turn against the other disc, until the outer surface if therim 10 and the sidewall of thegroove 12 wedge. The two rotor discs are then rigidly connected.FIG. 8 shows two such rotor discs after having been joined. To disconnect two rotor discs, this process is reversed. -
FIG. 8 also shows a plurality ofcooling ducts 14 that penetrate either anindividual rotor disc 1 or the stack of rotor discs. The wedged connection between rotor discs avoids welded connections between discs. Since it is no longer necessary to weld the rotor discs together, any risk of accidentally blocking the coolingduct 14 during welding is eliminated and more design flexibility of cooling channels is achieved. - The process of connecting rotor discs continued rotor discs may be continued until a stack of rotor discs is formed.
FIG. 5 shows such a stack. Also, heat treatment as explained above may be employed in order to increase the stiffness of the connection between rotor discs and utmost utilization of the material due to residual shrunk stress which acts as anti-centrifugal. - The disclosure describes a rotor made of rotor discs with interrupted screws in relation to a gas-turbine engine. In another embodiment, the same rotor and the same rotor discs form part of the rotor of a turbogenerator. Other applications such as hydro generators are also envisaged.
- Although the present invention has been fully described in connection with preferred embodiments, it is evident that modifications may be introduced within the scope thereof, not considering the application to be limited by these embodiments, but by the contents of the following claims.
Claims (15)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13162666.5 | 2013-04-08 | ||
EP13162666.5A EP2789797B1 (en) | 2013-04-08 | 2013-04-08 | Rotor |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140301851A1 true US20140301851A1 (en) | 2014-10-09 |
Family
ID=48082953
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/245,320 Abandoned US20140301851A1 (en) | 2013-04-08 | 2014-04-04 | Rotor |
Country Status (3)
Country | Link |
---|---|
US (1) | US20140301851A1 (en) |
EP (1) | EP2789797B1 (en) |
JP (1) | JP5855157B2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019160575A2 (en) * | 2017-08-02 | 2019-08-22 | Siemens Aktiengesellschaft | Induction heating for assembly and disassembly of the components in a turbine engine |
Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1107238A (en) * | 1914-06-27 | 1914-08-11 | Gen Electric | Rotor for elastic-fluid turbines. |
US1817808A (en) * | 1930-11-20 | 1931-08-04 | Spang Chalfant & Company Inc | Method of making tight threaded joints |
US1969431A (en) * | 1930-07-08 | 1934-08-07 | Byron Jackson Co | Safety tool joint |
US2284847A (en) * | 1940-04-03 | 1942-06-02 | Raymond Robert John | Photographic filter and like mount |
US2458148A (en) * | 1944-08-23 | 1949-01-04 | United Aircraft Corp | Rotor construction for turbines |
US2458149A (en) * | 1944-08-23 | 1949-01-04 | United Aircraft Corp | Rotor construction for turbines |
US2479057A (en) * | 1945-03-27 | 1949-08-16 | United Aircraft Corp | Turbine rotor |
US2479039A (en) * | 1944-11-06 | 1949-08-16 | United Aircraft Corp | Cast disk for turbine rotors |
US2656147A (en) * | 1946-10-09 | 1953-10-20 | English Electric Co Ltd | Cooling of gas turbine rotors |
US3094309A (en) * | 1959-12-16 | 1963-06-18 | Gen Electric | Engine rotor design |
US3916495A (en) * | 1974-02-25 | 1975-11-04 | Gen Electric | Method and means for balancing a gas turbine engine |
US5205716A (en) * | 1990-10-02 | 1993-04-27 | Societe Europeenne De Propulsion | Composite material turbine wheel |
US5338154A (en) * | 1993-03-17 | 1994-08-16 | General Electric Company | Turbine disk interstage seal axial retaining ring |
US6572337B1 (en) * | 1999-11-30 | 2003-06-03 | General Electric Co. | Turbine rotor torque transmission |
US6595751B1 (en) * | 2000-06-08 | 2003-07-22 | The Boeing Company | Composite rotor having recessed radial splines for high torque applications |
US20050000091A1 (en) * | 2001-11-22 | 2005-01-06 | Volvo Aero Corporation | Method for manufacturing a stator or rotor component |
US20120230797A1 (en) * | 2011-03-03 | 2012-09-13 | Phoenix Contact Gmbh & Co. Kg | Connection system of a housing of a plug connector having a nut |
US20130302163A1 (en) * | 2010-09-15 | 2013-11-14 | Wilson Solarpower Corporation | Method and apparatus for connecting turbine rotors |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB394001A (en) * | 1931-12-18 | 1933-06-19 | Parsons C A & Co Ltd | Improvements in and relating to built-up rotors, suitable for steam turbines |
NL66706C (en) * | 1944-10-06 | |||
CH257836A (en) * | 1947-08-07 | 1948-10-31 | Sulzer Ag | Rotors for centrifugal machines, in particular for gas turbines. |
DE1801398A1 (en) * | 1968-10-02 | 1970-10-01 | Aeg Kanis Turbinen | Runner of an axial flow machine |
GB1349170A (en) | 1970-07-09 | 1974-03-27 | Kraftwerk Union Ag | Rotor for a gas turbine engine |
US3922009A (en) * | 1974-07-05 | 1975-11-25 | Byron Jackson Inc | Coupling |
US4310286A (en) | 1979-05-17 | 1982-01-12 | United Technologies Corporation | Rotor assembly having a multistage disk |
JPS57193701A (en) * | 1981-05-25 | 1982-11-29 | Hitachi Ltd | Stacked rotor |
US5537814A (en) | 1994-09-28 | 1996-07-23 | General Electric Company | High pressure gas generator rotor tie rod system for gas turbine engine |
US7384075B2 (en) | 2004-05-14 | 2008-06-10 | Allison Advanced Development Company | Threaded joint for gas turbine components |
US8100666B2 (en) | 2008-12-22 | 2012-01-24 | Pratt & Whitney Canada Corp. | Rotor mounting system for gas turbine engine |
-
2013
- 2013-04-08 EP EP13162666.5A patent/EP2789797B1/en active Active
-
2014
- 2014-04-04 US US14/245,320 patent/US20140301851A1/en not_active Abandoned
- 2014-04-08 JP JP2014079251A patent/JP5855157B2/en not_active Expired - Fee Related
Patent Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1107238A (en) * | 1914-06-27 | 1914-08-11 | Gen Electric | Rotor for elastic-fluid turbines. |
US1969431A (en) * | 1930-07-08 | 1934-08-07 | Byron Jackson Co | Safety tool joint |
US1817808A (en) * | 1930-11-20 | 1931-08-04 | Spang Chalfant & Company Inc | Method of making tight threaded joints |
US2284847A (en) * | 1940-04-03 | 1942-06-02 | Raymond Robert John | Photographic filter and like mount |
US2458148A (en) * | 1944-08-23 | 1949-01-04 | United Aircraft Corp | Rotor construction for turbines |
US2458149A (en) * | 1944-08-23 | 1949-01-04 | United Aircraft Corp | Rotor construction for turbines |
US2479039A (en) * | 1944-11-06 | 1949-08-16 | United Aircraft Corp | Cast disk for turbine rotors |
US2479057A (en) * | 1945-03-27 | 1949-08-16 | United Aircraft Corp | Turbine rotor |
US2656147A (en) * | 1946-10-09 | 1953-10-20 | English Electric Co Ltd | Cooling of gas turbine rotors |
US3094309A (en) * | 1959-12-16 | 1963-06-18 | Gen Electric | Engine rotor design |
US3916495A (en) * | 1974-02-25 | 1975-11-04 | Gen Electric | Method and means for balancing a gas turbine engine |
US5205716A (en) * | 1990-10-02 | 1993-04-27 | Societe Europeenne De Propulsion | Composite material turbine wheel |
US5338154A (en) * | 1993-03-17 | 1994-08-16 | General Electric Company | Turbine disk interstage seal axial retaining ring |
US6572337B1 (en) * | 1999-11-30 | 2003-06-03 | General Electric Co. | Turbine rotor torque transmission |
US6595751B1 (en) * | 2000-06-08 | 2003-07-22 | The Boeing Company | Composite rotor having recessed radial splines for high torque applications |
US20050000091A1 (en) * | 2001-11-22 | 2005-01-06 | Volvo Aero Corporation | Method for manufacturing a stator or rotor component |
US20130302163A1 (en) * | 2010-09-15 | 2013-11-14 | Wilson Solarpower Corporation | Method and apparatus for connecting turbine rotors |
US20120230797A1 (en) * | 2011-03-03 | 2012-09-13 | Phoenix Contact Gmbh & Co. Kg | Connection system of a housing of a plug connector having a nut |
Also Published As
Publication number | Publication date |
---|---|
JP5855157B2 (en) | 2016-02-09 |
JP2014202213A (en) | 2014-10-27 |
EP2789797A1 (en) | 2014-10-15 |
EP2789797B1 (en) | 2018-08-08 |
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Legal Events
Date | Code | Title | Description |
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AS | Assignment |
Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SAFARI ZADEH, HOSSEIN;REEL/FRAME:032622/0901 Effective date: 20140407 |
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AS | Assignment |
Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, SWITZERLAND Free format text: CHANGE OF NAME;ASSIGNOR:ALSTOM TECHNOLOGY LTD;REEL/FRAME:038216/0193 Effective date: 20151102 |
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AS | Assignment |
Owner name: ANSALDO ENERGIA SWITZERLAND AG, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC TECHNOLOGY GMBH;REEL/FRAME:041686/0884 Effective date: 20170109 |
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STPP | Information on status: patent application and granting procedure in general |
Free format text: FINAL REJECTION MAILED |
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STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |