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
  • 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
• • 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
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/246—Fastening of diaphragms or stator-rings
• • 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
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/30—Exhaust heads, chambers, or the like
• • 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
• • 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
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/31—Application in turbines in steam turbines
• • 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
  • F05D2250/00—Geometry
  • F05D2250/20—Three-dimensional
• • 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
  • F05D2250/00—Geometry
  • F05D2250/50—Inlet or outlet
  • F05D2250/52—Outlet

Definitions

• the present invention relates to the field of turbine structural components (in particular steam or gas turbines) having working fluid output from an outer casing in radial direction.
• turbine structural components in particular steam or gas turbines
• the turbines (steam and gas, in particular) contain an inner body with a rotor (a flow portion) provided in the outer body.
• the outer body traps and guides the working fluid (steam, combustion products) being output from the inner body output after the last rotor vane phase.
• the outer body is provided with a radial working fluid drain.
• a steam turbine has a bottom drain provided with a condenser.
• a gas turbine has a top drain provided with a heat exchanger, if appropriate.
• a lateral outlet may be contemplated as well.
• the turbine inner body is provided with an annular deflector at output.
• the body is a rotary body (rotates around a machine axis) and all cross-sections thereof have the same shape.
• One of the tasks of the deflector is to guide and slow down flow, which results in change to working fluid pressure being output from the turbine inner body.
• the working fluid outputs from horizontally oriented turbine inner body in axial direction and upon passing a diffuser, trajectory of streamlines of the working fluid changes to radial direction. This is caused by restriction of its movement in axial direction using a rear wall of the inner body, or the deflector provided thereon.
• the problem may be eliminated by altering the shape of the turbine inner body.
• one solution includes volume increase of the inner body portion above the partitioning level. Then, the inner body may be flatter in the upper portion and extended in the area of the partitioning level.
• this solution brings higher costs.
• CN211819541U discloses an annular deflector of a steam turbine.
• the deflector has a rotary shape and provided with a mounting assembly for attaching to the turbine.
• the mounting assembly includes two cooperating arc-shaped fixing plates that fix the deflector onto the turbine by tightening each other.
• CN204175657 discloses an annular deflector for large-scale fans.
• the deflector has an enlarging funnel-shaped rotary shape with a flange with mounting bolt holes and allcircumference groove on the side of higher diameter.
• CN115008136 discloses a welding forming device for manufacture of an annular deflector for a turbine.
• the device includes a plurality of arc-shaped plates and a plurality of arc-shaped rods that support said plates.
• the device may be used for production of a deflector having a rotary shape.
• CN218151077 discloses a system for manual balancing of a steam turbine rotor by a mounting hole in a deflector.
• the deflector has a rotary shape and is provided with a closable hole through which a counterweight to each rotor vane may be either installed or demounted during the turbine shutdown.
• the present invention relates to shape of a turbine deflector.
• the deflector includes a collar having its base with a circular central hole that forms an interface for attaching of the deflector to output from the turbine inner body according to the prior art.
• the interface defines the plane YZ perpendicular to longitudinal axis of the turbine and of the deflector.
• the plane YZ is a vertical plane perpendicular to longitudinal axis of the turbine (i.e., to the turbine rotor rotation axis).
• the interface may be connected to the turbine inner body so that the deflector becomes an integral part of the turbine inner body (e.g., by welding, bonding, etc.).
• the interface may be provided with a flange having a central hole.
• the flange is provided with an internal bearing surface in the plane YZ for connection to the turbine inner body output, and with an outer surface by which it is connected to the collar.
• the flange may be then used to connect the deflector to the turbine internal body in a separable (e.g., screw) joint.
• the collar is a non-rotary shaped body comprising a flat profile, being either symmetrical or asymmetrical along the vertical XZ plane crossing turbine and deflector longitudinal axis, perpendicular to the plane YZ.
• a free edge of the flat profile being remote from the interface is shaped in the radial direction (i.e., in the direction from the turbine and deflector longitudinal axis) into a variable collar cross-section.
• variable collar cross-section comprises a plurality of forming curves of shapes being changed depending on a specific point on the collar circumference. All separate, mutually different collar profiles in the plurality of said radial planes follow each other seamlessly in the circumferential direction of the plane YZ. This means that the collar shape transitions are as smooth as possible without abrupt changes.
• At least first collar end has a deflector shape defined so that the forming curve, which forms the inner collar surface, has:
• the intermediate point XI is the only point of relevant forming curve in which a tangent of the forming curve is parallel to the plane YZ. Perpendicular distance of the intermediate point XI from the plane YZ is highest of all points of said forming curve. This is the distance in the direction from the turbine inner body; the plane crossing the end point X2, which is parallel to the plane YZ, is located between the plane YZ and the intermediate point XI.
• the intermediate point XI is the most distant point from the turbine inner body downstream the working fluid after output from the turbine inner body.
• said definitions about mutual position of the points XO, XI, and X2 apply to any of said plurality of the forming curves that jointly form the inner collar surface.
• variable collar cross-section increases in axial direction (i.e., in the direction from the interface to the intermediate points XI of the forming curves) so that the collar has a funnellike shape extending from the interface.
• the collar inner surface defines an extending volume through which the working fluid (steam, combustion products, and more) moves through diffuser central hole from the turbine inner body output.
• the deflector cross-section in the plane XZ is axially asymmetrical according to the plane XY crossing the turbine and deflector longitudinal axis being perpendicular to the XZ and YZ planes. At the same time, the cross-section in the plane XZ differs from the one in the plane XY.
• An intersection point of the plane XY with the plane XZ in the plane YZ is the geometrical centre of the diffuser central hole in the plane YZ.
• the end points X2 of two forming curves in the plane XZ are located on the end points X2 line being concurrent to the plane YZ.
• the plane YZ contains the intersection point with the end points X2 line.
• the end points X2 line forms acute angle a with the plane YZ.
• the perpendicular distance between the forming curve end point X2 and the plane YZ is lower on the first collar edge than the perpendicular distance between the forming curve end point X2 of the opposite second collar edge and the plane YZ.
• the intermediate points XI of two forming curves in the plane XZ are located on the intermediate points XI line being concurrent to the plane YZ as well.
• the plane YZ contains the intersection point with the intermediate points XI line.
• the intermediate points XI line also forms acute angle a’ with the plane YZ.
• the perpendicular distance of the end point X2 of the first collar edge in the plane XZ from the plane XY (or from the central axis O) is lower than the perpendicular distance of the end point X2 of the second collar edge.
• a portion of the generic forming curve with zero curvature and a finite length may be in the plane XZ and perpendicular to the plane YZ. This is the portion of the generic forming curve facing from the initial point XO to the intermediate point XI. Therefore, a portion of the collar inner surface is a portion of a cylindrical surface at that location. Considering the line crossing the end points X2 of both collar edges, which is not parallel in the plane XZ with the interface, the cylindrical surface obviously narrows down towards the first collar edge. This embodiment may be favourable in an application where the axial space for flowing out the working fluid between turbine inner and outer body is higher.
• the first collar edge in the plane XZ is that one being remote from the drain of the working fluid from the outer body.
• the second collar edge is directed to the working fluid drain from the outer body.
• the first collar edge is the upper one in the plane XZ.
• the first collar edge is the lower one in the plane XZ.
• the present invention aims for changing a trajectory of individual streamlines of a flow field using a suitable deflector shape upon output from the turbine inner body, and to reduce unevenness of the flow field.
• the flow field modelling achieves loss reduction due to reduced speed of the flow field after the diffuser.
• the liquid flow then flows more efficiently between the turbine inner and outer body because the effective cross-section between the bodies increases.
• the other positive results include increased turbine performance, vibration, and noise reduction.
• Reduced unevenness of the flow field in circumferential direction in the working space of the vanes increases their life, and the turbine will have higher working range.
• the effective cross-section between the bodies through which the fluid flows is increased due to the moderation of the flow field.
• the outer body can be reduced at the turbine design stage to achieve cost savings.
• the deflector is usable for steam turbines, gas turbines, etc.
• the collar is modified, negative manifestations of liquid back flow mixing with the main flow are prevented. Forming of eddies, which produce loss, is eliminated thereby.
• a suitable collar shape creates a space that expands on the circumference towards the working fluid drain from the side opposite the working fluid drain from the outer body. Thereby, the space for the working fluid drain, which is not disturbed by the working fluid flowing from the turbine output, is created. Said diffuser shape makes the flow field uniform and models the flow field without any negative manifestations.
• Fig: 1 - is external view in the plane XZ to a deflector embodiment having a rotary shape according to the prior art
• Fig. 2 - is external view in the plane XZ to another deflector embodiment having a rotary shape according to the prior art
• Fig. 3 - is external view in the plane XZ to a deflector according to the present invention
• Fig. 4 - is external view in the plane XZ to a deflector according to the present invention having a portion of a forming curve with zero curvature and a finite length perpendicular to the plane YZ;
• Fig. 5 - is front axial view in the plane YZ to a deflector according to the present invention
• Fig. 6 - is cross-section view in the plane XZ to the deflector according to the present invention.
• Fig. 7 - is close up sectional view according to Fig. 6 showing the first collar edge
• Fig. 8 - is sectional view in the plane XZ to the deflector according to the present invention showing lines P and P’ and distances between end points of the forming curves and the plane YZ.
• a turbine deflector described in this example is intended for a steam turbine having a bottom working fluid drain from an outer body to a condenser.
• the deflector includes an interface 6 in the form of a flange 1_ with a central hole.
• the flange j_ is provided with an inner bearing surface 4 in the plane YZ for attachment to an output 2 from a turbine inner body.
• the flange 1_ is provided with an outer surface 5 to which a collar 3 with increasing cross-section of the central hole is attached.
• Shape of the collar 3 is defined in lateral cross-section by a plurality of generic forming curves k forming the collar 3 inner surface.
• the deflector has a non-rotary shape defined so that the collar 3 profile in the cross-section in the plane XZ is axially asymmetrical along the plane XY and differs from the lateral cross-section in the plane XY.
• the cross-section in the plane XZ is vertical one
• the cross-section in the plane XY is horizontal one. All separate, mutually different cross-sections of the collar 3 profiles follow each other seamlessly in the circumferential direction of the plane YZ.
• An intersection point of the plane XY with the plane XZ in the plane YZ is a geometrical centre of a circular central hole of the flange 1 in the turbine and deflector longitudinal axis O.
• the generic forming curve k initial point XO lies in the intersection of the collar 3 and the interface 6
• an end point X2 being the generic forming curve k end point, has the highest distance from the longitudinal turbine and deflector axis Q of all points on said generic forming curve k
• an intermediate point XI between the initial point XO and the end point X2 having perpendicular distance from the plane YZ highest of all points of the generic forming curve k has the distance from the turbine and deflector longitudinal axis Q higher than the distance of the initial point XO and lower than the distance of the end point X2.
• the distance of the generic forming curve k initial point X2 of a first (here, upper) collar 3 edge 31 from the plane XY is lower than the generic forming curve k end point X2 of second (here, bottom) collar 3 edge 32.
• the line P crossing the generic forming curve k end point X2 of the first collar 3 edge 31 and the generic forming curve k end point X2 of the second collar 3 edge 32 in the plane XZ is not parallel to the inner flange 1 bearing surface 4 in the plane YZ.
• the line P’ crossing the generic forming curve k intermediate point XI of the first collar 3 edge 31 and the generic forming curve k intermediate point XI of the second collar 3 edge 32 in the plane XZ is not parallel to the inner flange 1_ bearing surface 4 in the plane YZ.
• the perpendicular distance Cl between the generic forming curve k end point X2 of the first collar 3 edge 31 and the plane YZ is lower than the perpendicular distance C2 between the generic forming curve k end point X2 of the second collar 3 edge 32 and the plane YZ.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Hydraulic Turbines (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=90826669

Family Applications (1)

Country Status (4)

Family Cites Families (8)

• 2023
  • 2023-03-02 CZ CZ2023-83A patent/CZ202383A3/cs unknown
• 2024
  • 2024-03-01 WO PCT/CZ2024/050011 patent/WO2024179628A1/en not_active Ceased
  • 2024-03-01 KR KR1020257033247A patent/KR20250155612A/ko active Pending
  • 2024-03-01 EP EP24720748.3A patent/EP4673631A1/en active Pending

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