Classifications

• • H—ELECTRICITY
  • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
  • H02K—DYNAMO-ELECTRIC MACHINES
  • H02K3/00—Details of windings
  • H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
  • H02K3/24—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
• • H—ELECTRICITY
  • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
  • H02K—DYNAMO-ELECTRIC MACHINES
  • H02K9/00—Arrangements for cooling or ventilating
  • H02K9/08—Arrangements for cooling or ventilating by gaseous cooling medium circulating wholly within the machine casing

Definitions

• the present invention relates to a structure for enhanced cooling of generator rotors by distributing more coolant towards the normally starved center of the cavity.
• the power output rating of dynamoelectric machines is often limited by the ability to provide additional current through the rotor field winding because of temperature limitations imposed on the electrical conductor insulation. Therefore, effective cooling of the rotor winding contributes directly to the output capability of the machine. This is especially true of the rotor end region, where direct, forced cooling is difficult and expensive due to the typical construction of these machines. As prevailing market trends require higher efficiency and higher reliability in lower cost, higher-power density generators, cooling the rotor end region becomes a limiting factor.
• Turbo-generator rotors typically consist of concentric rectangular coils mounted in slots in a rotor.
• the end portions of the coils (commonly referred to as endwindings), which are beyond the support of the main rotor body, are typically supported against rotational forces by a retaining ring (see FIGURE
• Support blocks are placed intermittently between the concentric coil endwindings to maintain relative position and to add mechanical stability for axial loads, such as thermal loads (see FIGURE 2).
• axial loads such as thermal loads (see FIGURE 2).
• the copper coils are constrained radially by the retaining ring on their outer radius, which counteracts centrifugal forces.
• the presence of the spaceblocks and retaining ring results in a number of coolant regions exposed to the copper coils.
• the primary coolant path is axial, between the spindle and the bottom of the endwindings.
• discrete cavities are formed between coils by the bounding surfaces of the coils, blocks and the inner surface of the retaining ring structure.
• the endwindings are exposed to coolant that is driven by rotational forces from radially below the endwindings into these cavities (see FIGURE 3).
• This heat transfer tends to be low. This is because according to computed flow pathlines in a single rotating end winding cavity from a computational fluid dynamic analysis, the coolant flow enters the cavity, traverses through a primary circulation and exits the cavity. Typically, the circulation results in low heat transfer coefficients especially near the center of the cavity. Thus, while this is a means for heat removal in the endwindings, it is relatively inefficient.
• Some systems penetrate the highly stressed rotor retaining ring with radial holes to allow cooling gas to be pumped directly alongside the rotor endwindings and discharged into the air gap, although such systems can have only limited usefulness due to the high mechanical stress and fatigue life considerations relating to the retaining ring.
• Passive cooling provides the advantage of minimum complexity and cost, although heat removal capability is diminished when compared with the active systems of direct and forced cooling.
• Any cooling gas entering the cavities between concentric rotor windings must exit through the same opening since these cavities are otherwise enclosed - the four "side walls" of a typical cavity are formed by the concentric conductors and the insulating blocks that separate them, with the "bottom” (radially outward) wall formed by the retaining ring that supports the endwindings against rotation. Cooling gas enters from the annular space between the conductors and the rotor spindle. Heat removal is thus limited by the low circulation velocity of the gas in the cavity and the limited amount of the gas that can enter and leave these spaces.-
• the cooling gas in the end region has not yet been fully accelerated to rotor speed, that is, the cooling gas is rotating at part rotor speed.
• the heat transfer coefficient is typically highest near the spaceblock that is downstream relative to the flow direction - where the fluid enters with high momentum and where the fluid coolant is coldest.
• the heat transfer coefficient is also typically high around the cavity periphery. The center of the cavity receives the least cooling.
• the invention provides a structure and method for enhancing cooling of the generator rotor by directing coolant flow towards the center of the cavities defined by and between the concentric rotor endwindings and the support blocks.
• At least one deflector is mounted to the face of the spaceblock disposed on the downstream side of the cavity to redistribute coolant flow towards the center of the cavity. More specifically, the invention provides at least one deflector structure on the downstream face of at least one of the spaceblocks in a generator rotor endwinding assembly so as to redistribute flow in the respective cavity towards the normally starved center of the cavity, thus, substantially increasing heat transfer performance in the rotating assembly.
• the deflector extends substantially axially of the associated spaceblock to intercept a substantial portion of the coolant flow that reaches and/or flows along the radially inner portions of the spaceblock. That intercepted flow is redirected towards the center of the cavity. Coolant flow that flows generally directly to the spaceblocks radially outside the deflector structure will continue in its generally traditional circular flow path. According to an alternate embodiment of the invention, the deflector structure spans only a portion of the axial dimension or depth of the cavity. This allows some high momentum coolant to reach the outer radial corner of the cavity and directs the remainder of the coolant towards the center of the cavity.
• the partial depth deflector may be disposed to span the part depth of the cavity from adjacent one endwinding wall of the cavity, adjacent the other endwinding wall of the cavity or generally centrally of its associated spaceblock. In this embodiment, the deflector spans about one half of the depth of the associated spaceblock.
• two or more axially aligned deflector structures are provided, each spanning a portion of the axial dimension or depth of the cavity. This allows some high momentum coolant to flow between axially adjacent deflector structures to reach the outer radial corner of the cavity and directs the remainder of the coolant towards the center of the cavity.
• FIGURE 1 is a cross-sectional view of a portion of the end turn region of a dynamoelectric machine rotor with stator in opposed facing relation thereto;
• FIGURE 2 is a cross-sectional top view of the dynamoelectric machine rotor taken along line 2-2 of FIGURE 1 ;
• FIGURE 3 is a schematic illustration showing passive gas flow into and through endwinding cavities
• FIGURE 4 is a perspective view, partly broken-away of a portion of the rotor end turn region in accordance with a first embodiment of the invention disclosed in U.S. Patent No. 5,644,179;
• FIGURE 5 is a perspective view, partly broken away, of a portion of the rotor end turn region showing a second embodiment of the invention of U.S. Patent No. 5,644,179;
• FIGURE 6 is a cross-sectional view illustrating a deflector as an embodiment of the invention provided on the downstream side of a spaceblock to deflect coolant towards the normally starved center of the cavity;
• FIGURE 7 illustrates an alternate embodiment of the invention wherein at least one deflector is provided to each only partially span the depth of the cavity to allow some of the coolant to easily pass to the outer radial extent of the cavity while deflecting a portion of the coolant towards the cavity center.
• FIGURES 1 and 2 show a rotor 10 for a gas-cooled dynamoelectric machine, which also includes a stator 12 surrounding the rotor.
• the rotor includes a generally cylindrical body portion 14 centrally disposed on a rotor spindle 16 and having axially opposing end faces, of which a portion 18 of one end face is shown in FIGURE 1.
• the body portion is provided with a plurality of circumferentially- spaced, axially extending slots 20 for receiving concentrically arranged coils 22, which make up the rotor winding. For clarity, only five rotor coils are shown, although several more are commonly used in practice.
• a number of conductor bars 24 constituting a portion of the rotor winding are stacked in each one of the slots. Adjacent conductor bars are separated by layers of electrical insulation 22.
• the stacked conductor bars are typically maintained in the slots by wedges 26 (FIGURE 1) and are made of a conductive material such as copper.
• the conductor bars 24 are interconnected at each opposing end of the body portion by end turns 27, which extend axially beyond the end faces to form stacked endwindings 28. The end turns are also separated by layers of electrical insulation.
• a retaining ring 30 is disposed around the end turns at each end of the body portion to hold the endwindings in place against centrifugal forces.
• the retaining ring is fixed at one end to the body portion and extends out over the rotor spindle 16.
• a centering ring 32 is attached to the distal end of the retaining ring 30. It should be noted that the retaining ring 30 and the center ring 32 can be mounted in other ways, as is known in the art.
• the inner peripheral edge of the centering ring 32 is radially spaced from the rotor spindle 16 so as to form a gas inlet passage 34 and the endwindings 28 are spaced from the spindle 16 so as to define an annular region 36.
• a number of axial cooling channels 38 formed along slots 20 are provided in fluid communication with the gas inlet passage 34 via the annular-region 36 to deliver cooling gas to the coils 22.
• the endwindings 28 at each end of the rotor 10 are circumferentially and axially separated by a number of spacers or spaceblocks 40. (For clarity of illustration, the spaceblocks are not shown in FIGURE 1 ).
• the spaceblocks are elongated blocks of an insulating material located in the spaces between adjacent endwindings 28 and extend beyond the full radial depth of the endwindings into the annular gap 36. Accordingly, the spaces between the concentric stacks of the end turns 27 are divided into cavities. These cavities are bounded on the top by the retaining ring 30 and on four sides by adjacent endwindings 28 and adjacent spaceblocks 40, as shown in FIGURE 3.
• each of these cavities is in fluid communication with the gas inlet passage 34 via the annular region 36.
• a portion of the cooling gas entering the annular region 36 between the endwinding 28 and the rotor spindle 16 through the gas inlet passage 34 thus enters the cavities 42, circulates therein, and then returns to the annular region 36 between the endwinding and the rotor spindle. Air flow is shown by the arrows in FIGURES 1 and 3.
• FIGURE 3 The inherent pumping action and rotational forces acting in a rotating generator cavity typically produce a large single flow circulation cell, as schematically shown in FIGURE 3.
• This flow circulation cell exhibits its highest velocity near the peripheral edges of the cavity, leaving the center region inadequately cooled due to the inherently low velocity in the center region of the cavity.
• large areas of the corner regions are also inadequately cooled because the circular motion of the flow cell does not carry cooling flow into the corners.
• each spaceblock 140 is provided with a deflector structure 144 on the surface 146 thereof disposed on the downstream side of the respective cavity (hereinafter downstream surface) for redistributing coolant flow to the center of the respective cavity 142 to increase the heat transfer coefficient there.
• Each deflector structure 144 has a lower generally curved surface 148 for intercepting and redirecting flow as shown by arrow A.
• the upper surface 150 is generally planer so that the deflector defines a generally thin flow facing edge 152 so as to effectively intercept flow without unnecessary pressure loss.
• cooling gas inlet 34 (FIGURE 1) into the annular region 36 between the end winding 28 and the rotor spindle 16.
• a kinetic pressure head is present which drives the cooling gas toward the downstream side 146 of the cavity 142 in a generally circular flow.
• the deflector 144 at least a portion of the coolant flow is intercepted by the deflector 144 and redirected as shown by arrow A to the central region of the cooling cavity 142, which would otherwise be generally starved of coolant flow. Coolant flow that is not intercepted by the deflector continues in its generally circulatory flow as shown by arrow B.
• a single flow deflector is provided that spans a substantial portion of the depth or axial dimension of the cavity, for example, at least about 75% and more preferably on the order of 100% of the depth of the cavity.
• FIGURE 7 shows a partial section of the rotor endwinding showing the cavities 242 defined between the spaceblocks 240 and with the direction with rotation indicated by arrow X.
• at least one deflector structure 244 is provided to deflect coolant flow to the central region of the adjacent cavity.
• the defector structure(s) 244 are provided on the downstream surface 246 of at least one spaceblock 240.
• each deflector 244 extends only a part depth or part axially of the spaceblock so as to leave at least one a vertical flow region for some high momentum circulating coolant flow to reach the outer radial corner of the cavity while the remainder of the coolant is deflected towards the center of the cavity.
• a partial, depth deflector may be disposed to span the part depth of the cavity from adjacent one endwinding wall of the cavity, adjacent the other endwinding wall of the cavity, or generally centrally of its associated spaceblock.
• a single deflector 244 is provided to span about one half of the depth of the associated spaceblock.
• two or more axially aligned deflector structures are provided, each spanning a portion of the axial dimension or depth of the cavity. In this manner, at least one vertical flow region is reserved for high momentum circulating coolant flow to reach the outer radial corner of the cavity while the remainder of the coolant is deflected towards the center of the cavi.ty.
• the coolant flow into the respective cavity 242 will flow to and begin its flow radially outwardly along the spaceblock surface 246.
• a portion of that flow is intercepted and deflected by the deflector structure(s) 244 toward the central region of the respective cavity as shown by arrow A.
• the remainder of the coolant flow bypasses the deflector structure because of the gaps defined by its truncated axial length and continues up and radially outwardly along the spaceblock, as shown by arrow C, for continuing as circulating flow, as shown by arrow B.
• the deflected flow and the non- deflected flow are rejoined at the upstream side of the cavity to continue in a clockwise direction, in the illustrated embodiment, below and around the spaceblock 240 to the next sequential cavity 242.
• the deflector 144, 244 extends at least about 20% and more preferably at least about 25% of the circumferential dimension of the cooling cavity so as to effectively intercept and redirect the flow towards the central region of the cavity, rather than merely causing surface turbulation.
• the curved configuration of the lower surface 148, 248 of the deflector enhances the deflector function.

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• Engineering & Computer Science (AREA)
• Power Engineering (AREA)
• Motor Or Generator Cooling System (AREA)
• Windings For Motors And Generators (AREA)

Priority Applications (6)

Applications Claiming Priority (2)

Publications (2)

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Family Applications (1)

Country Status (12)

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• 2000
  • 2000-12-19 US US09/739,359 patent/US6465917B2/en not_active Expired - Fee Related
• 2001
  • 2001-11-30 DE DE60115494T patent/DE60115494T2/de not_active Expired - Lifetime
  • 2001-11-30 MX MXPA02008084A patent/MXPA02008084A/es active IP Right Grant
  • 2001-11-30 ES ES01987183T patent/ES2250506T3/es not_active Expired - Lifetime
  • 2001-11-30 WO PCT/US2001/045299 patent/WO2002050982A2/en not_active Ceased
  • 2001-11-30 EP EP01987183A patent/EP1346457B1/en not_active Expired - Lifetime
  • 2001-11-30 AU AU2002239423A patent/AU2002239423A1/en not_active Abandoned
  • 2001-11-30 CN CNB01805272XA patent/CN100352142C/zh not_active Expired - Fee Related
  • 2001-11-30 JP JP2002552170A patent/JP3727923B2/ja not_active Expired - Fee Related
  • 2001-11-30 CA CA002399347A patent/CA2399347C/en not_active Expired - Fee Related
  • 2001-11-30 KR KR10-2002-7010647A patent/KR100467388B1/ko not_active Expired - Fee Related
  • 2001-11-30 CZ CZ20022716A patent/CZ303848B6/cs not_active IP Right Cessation

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