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1. WO2020142142 - TURBINE BLADE WITH A COUPLED SERPENTINE CHANNEL

Note: Text based on automatic Optical Character Recognition processes. Please use the PDF version for legal matters

[ EN ]

Claims

1. A turbine blade (440) for use in a gas turbine engine (100), the turbine blade comprising:

a base (442) including

a root end (444); and

an airfoil (441) comprising

a skin (460) extending from the base and defining a first edge (446, 447), a second edge (446, 447) opposite the first edge, a pressure side (448), and a lift side (449) opposite the pressure side, and having a tip end (445) opposite from the root end,

a base rib (490a, 490b) disposed within the airfoil and the base, extending from the base and into the airfoil, and having a base rib end (491a, 491b) disposed opposite from the base,

a center divider (492a, 492b) extending from adjacent the first edge towards the second edge, disposed between the base rib and the tip end, a center rib (493a, 493b) disposed between the center divider and the second edge, extending from adjacent the center divider towards the tip end and extending from adjacent the center divider towards the root end, the center rib disposed between the root end and the tip end and at least partially between the base rib and the second edge, and having

a center rib tip end (495a, 495b) disposed at the tip end of the center rib, and

a center rib base end (494a, 494b) disposed opposite from the tip end,

a tip center rib (498a, 498b) extending from adjacent the second edge towards the first edge, disposed between the center rib and the tip end,

a tip rib (496a, 496b) extending from adjacent the tip center rib, distal to the second edge, towards the base, the tip rib disposed at least partially between the center rib and the first edge, disposed between the center divider and the tip end, and having a tip rib end (497a, 497b) disposed opposite from the tip end, and

a dividing rib (480a, 480b) extending from proximate an interface of the airfoil and the base, towards the tip end while between the first edge and the base rib, to between the tip rib and the first edge and between the tip end and the center divider, and having a dividing rib tip end (483a, 483b) disposed proximate and spaced from the tip end; and

a first channel (474a, 474b) beginning proximate the interface of the airfoil and the base, the first channel extending to the center divider while between the first edge and the dividing rib, the first channel further extends around the base rib tip, between the dividing rib and the center divider, and further to between the dividing rib and the center rib, the first channel further extends toward the root end while located between the dividing rib and the center rib, the first channel further extends around the center rib base end while between the center rib and the dividing rib, towards the tip end while between the center rib and the dividing rib, the first channel further extends towards the tip end while between the center rib and the dividing rib, the first channel further extends around the center rib tip end while between the center rib and dividing rib, towards the base while between the dividing rib and the center rib, the first channel further extends to the center divider while between the dividing rib and center rib, the first channel further extends around the tip rib end while between the dividing rib and the center divider, to between the dividing rib and the first edge, the first channel further extends towards the tip end, between the first edge and the dividing rib.

2. The turbine blade of claim 1, the turbine blade further comprising a second channel (476a, 476b) beginning proximate the interface of the airfoil and the base, the second channel extending from between the dividing rib and the base rib to the center divider, the second channel further extends around the base rib end, to between the base rib and the dividing rib, and further towards the base, the second channel further extends towards the root end while located between the base rib and the dividing rib, the second channel further extends around the center rib base end between the dividing rib and the root end, to between the dividing rib and the second edge, the second channel further extends to the tip center rib while between the dividing rib and the second edge, the second channel further extends around the center rib tip end while between the dividing rib and the tip center rib, to between the tip rib and the dividing rib, the second channel further extends towards the center divider while between the tip rib and dividing rib, the second channel further extends around the tip rib end while between the tip rib and the dividing rib, towards the tip end, the second channel further extends towards the tip end, between the dividing rib and the tip rib.

3. The turbine blade of claim 1, wherein the center rib and the dividing rib extend into the base.

4. The turbine blade of claim 1, the dividing rib further comprising

a dividing rib lower first edge portion (510a, 510b) extending from proximate to an interface of the airfoil and the base, towards the center divider while between the first edge and the base rib,

a dividing rib lower first edge transition portion (513a, 513b) extending from between the first edge and base rib, to between the base rib and the center divider, and further to between the base rib and the center rib,

a dividing rib lower middle portion (514a, 514b) extending from between the base rib and center rib towards the root end while located between the base rib and the center rib,

a dividing rib lower middle transition portion (517a, 517b) extending from between the base rib and the center rib, to between the center rib and the root end, and further to between the center rib and the second edge,

a dividing rib second edge portion (518a, 518b) extending from between the center rib and the second edge towards the tip center rib,

a dividing rib second edge transition portion (522a, 522b) extending from between the second edge and the center rib, to between the center rib and the tip center rib, and further to between the tip rib and the center rib, a dividing rib upper middle portion (523a, 523b) extending from between the tip rib and center rib towards the center divider,

a dividing rib upper middle transition portion (526a, 526b) extending from between the tip rib and center rib, to between the tip rib and the center divider, and further to between the tip rib and the first edge, and

a dividing rib upper first edge portion (527a, 527b) extending from between the first edge and the tip rib towards the tip end.

5. The turbine blade of claim 4, wherein the dividing rib lower first edge transition extends from the dividing rib lower first edge portion, the dividing rib lower middle portion extends from the dividing rib lower first edge transition portion, the dividing rib lower middle transition portion extends from the dividing rib lower middle portion, the dividing rib second edge portion extends from the dividing rib lower middle transition portion, the dividing rib second edge transition portion extends from the dividing rib second edge portion, the dividing rib upper middle portion extends from the dividing rib second edge transition portion, the dividing rib upper middle transition portion extends from the dividing rib upper portion, the dividing rib upper first edge portion extends from the dividing rib upper middle transition portion.

6. The turbine blade of claim 1, the center divider further comprising

a center divider transition (475a, 475b) extending from the center divider to the first edge towards the second edge, that is wider adjacent the first edge than opposite from the first edge, and

a center rib transition (477a, 477b) disposed opposite from the center divider transition, extending from the center divider to the center rib towards the first edge, which is wider adjacent the center rib than opposite the center rib.

7. The turbine blade of claim 2, the turbine blade further comprising

a main inlet (462a, 462b) disposed in the base and in flow communication with the first channel and the second channel, and

a secondary inlet (464a, 464b) disposed in the base and in flow communication with the second channel.

8. The turbine blade of claim 7, the turbine blade further comprising a metering plate blocking plate disposed radially inward of the main inlet, the metering plate (504a) having

a first metering orifice (508a) sized to provide a desired amount or flow of cooling air to the first channel, and

a second metering orifice (509a) sized to provide a desired amount or flow of cooling air to the second channel.

9. The turbine blade of claim 7, wherein the dividing rib lower first edge portion extends from main inlet to between the base rib and the first edge.

10. The turbine blade of claim 1, wherein the turbine blade includes a tip opening (503a, 503b) that is defined by the space between the pressure side of the skin, the lift side of the skin, the tip center rib, and a trailing edge (447). The tip opening operable to allow for cooling air to escape the airfoil near the tip end.