摘要:
A steam turbine nozzle singlet (40) having a blade or airfoil (42) between inner and outer sidewalls (44, 46) is provided. The sidewalls include steps or flanges (56, 58) which are received in complementary recesses in the rings enabling axially short low heat input welds e.g., e-beam welds. These complementary steps and recesses mechanically interlock the singlet between the rings preventing displacement of the singlet in the event of weld failure. The low heat input welds minimize or eliminate distortion of the nozzle flow path. Additional features on the singlets, provide a datum for milling machines to form singlets of different sizes.
摘要:
Various aspects include an alignment key (26) for a turbomachine (20), along with a turbomachine (20) including the alignment key (26) and a related storage medium. In some cases, the alignment key (26) includes: a body (32) having primary axis (a p ) and sized to engage a diaphragm slot (28) in the turbomachine (20), the body (32) having sidewalls (34) extending along the primary axis (a p ); a chamfered tip section (36) continuous with the body (32), the chamfered tip section (36) sized to engage a casing slot (30) in the turbomachine (20); and a slot (40) extending through the body (32)and the chamfered tip section (36), the slot (40) having a first opening (42) proximate an end of the body (32) and a second opening (45) proximate the chamfered tip section (36), wherein the sidewalls (34) of the body (32) taper from the end of the body (32) toward the chamfered tip section (36).
摘要:
The invention is related to a rotor key member (20) for retaining a circumferential seal (24) in a steam turbine rotor assembly (22). The rotor key member (20) includes a body (26) comprising a chamfered edge (36) and a pair of opposing side (28). A circumferential seal (24) is inserted into a primary slot (50) within a rotor body (46). The rotor key member (20) is inserted into into a secondary slot (52) being arranged in the circumferential seal (24) and the rotor body (46). The rotor key member (20) may on its upper surface form a pocket (38) in which a weld (40) may be formed. Alternatively, the rotor key member (20) may be secured by interlocking with a respective slot (43) in the circumferential seal (24) Thus, circumferential locking and a consistent sealing across the entire circumference of the steam turbine rotor assembly is provided.
摘要:
The invention is related to a rotor key member (20) and a related steam turbine rotor assembly (22). The rotor key member (20) for circumferentially retaining a circumferential seal (24) in a steam turbine rotor body (46) comprises a main body (26), sized to contact an axial face (56) of the circumferential seal (24), and a locking member (28), extending from the main body (26) in an axial direction toward the circumferential seal (24). The locking member (28) has at least one circumferential edge (29) sized to complement a corresponding slot (30) in the circumferential seal (24) to restrict movement of the circumferential seal (24) relative to the steam turbine rotor body (46).
摘要:
The invention is related to a rotor key member (20), along with a related steam turbine rotor assembly assembly (22). The rotor key member (20) for retaining a circumferential seal (24) includes a main body (26), a first arm (28) extending from the main body (26), a second arm (30) extending from the main body (26), wherein the first arm (28), the second arm (30) and the main body (26) define a space (32) spanning axially (A) between the first arm (28) and the second arm (30) and a hook (34) extending from the second arm (30) in a direction axially away from the space, the hook (34) sized to contact a radially inner surface (36) of the circumferential seal (24). With the above configuration the rotor key member (20) restrains the cirumferential seal (24) in a slot (48) in the rotor body (46) of a steam turbine rotor.
摘要:
A rotor assembly (300) includes a rotor (34) having a dovetail slot (36). The dovetail slot (36) includes a plurality of recesses (44) and a first radially innermost surface (210). A rotor blade (20) includes an airfoil (22) that extends radially outward from a platform (31) and a dovetail (32) that extends radially inward from the platform (31). The dovetail (32) includes a plurality of projections (40) extending in opposite directions that are received by the plurality of recesses (44) of the dovetail slot (36). The second radially innermost surface (46) defines a groove (33) from the leading edge surface (25) to the trailing edge surface (27). The shim (52) is positioned within the groove (33) and between the first radially innermost surface (210) of the dovetail slot (36) and the second radially innermost surface (46) of the dovetail (32). The shim (52) extends at least partially radially along both of the leading edge surface (25) and the trailing edge surface (27) to secure the rotor blade (20) within the dovetail slot (36) during various operating conditions of the turbomachine.