Turbine nozzle vane

• US 6,491,493 B1
• Filed: 02/01/2001
• Issued: 12/10/2002
• Est. Priority Date: 06/12/1998
• Status: Expired due to Term

• Current Assignee: Ebara Corporation
• Original Assignee: Ebara Corporation
• Inventors: Watanabe, Hiroyoshi, Harada, Hideomi
• Primary Examiner(s): Ryznic, John E.
• Application Number:
  US09/719,398
• Time in Patent Office: 677 Days
• Field of Search: 415/191, 415/192, 415/208.1, 415/208.2, 415/209.1, 415/209.4, 415/210.1
• US Class Current: 415/191
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68

Abstract

A turbine nozzle comprises an array of nozzle blades (1) U disposed circumferentially in an annular passage (4) defined between inner and outer rings of a diaphragm and fixed to the inner and outer rings of the turbine diaphragm. The flow passage is defined between a pressure surface (F) and a suction surface (B) of adjacent ones of the nozzle blades, and a cross section of the flow passage includes predetermined ranges extending along a blade height (h) from the inner and outer diameter surfaces (hub and tip end walls) and defined by a curved line, and another range defined by a substantially straight line.

Claims

1. A turbine nozzle comprising:

an array of nozzle blades disposed circumferentially in an annular passage defined between a hub end wall of an inner ring and a tip end wall of an outer ring and fixed to said hub and tip end walls; and

a flow passage defined between a pressure surface and a suction surface of adjacent ones of said nozzle blades, a cross section of said flow passage within a predetermined region from a leading edge of the nozzle blade in the meridional direction comprising a curved line on each of said pressure surface and said suction surface in a predetermined range of the blade height inwardly from said hub and tip end walls and a substantially straight line on each of said pressure surface and said suction surface in another range,

wherein said predetermined range comprises a range corresponding to 20 to 40% of said blade height inwardly from said hub and tip end walls.

2. A turbine nozzle comprising:

an array of nozzle blades disposed circumferentially in an annular passage defined between a hub end wall of an inner ring and a tip end wall of an outer ring and fixed to said hub and tip end walls; and

a flow passage defined between a pressure surface and a suction surface of adjacent ones of said nozzle blades, a cross section of said flow passage within a predetermined region from a leading edge of the nozzle blade in the meridional direction comprising a curved line on each of said pressure surface and said suction surface in a predetermined range of the blade height inwardly from said hub and tip end walls and a substantially straight line on each of said pressure surface and said suction surface in another range,

wherein said predetermined region comprises a region from said leading edge of said nozzle blade to a position of at least 30% of the blade width in the meridional direction.

3. A turbine nozzle comprising:

an array of nozzle blades disposed circumferentially in an annular passage defined between a hub end wall of an inner ring and a tip end wall of an outer ring and fixed to said hub and tip end walls; and

a flow passage defined between a pressure surface and a suction surface of adjacent ones of said nozzle blades, a cross section of said flow passage within a predetermined region from a leading edge of the nozzle blade in the meridional direction comprising a curved line on each of said pressure surface and said suction surface in a predetermined range of the blade height inwardly from said hub and tip end walls and a substantially straight line on each of said pressure surface and said suction surface in another range,

wherein said cross section of said flow passage within a range from said leading edge of said nozzle blade to a position of at least 30% of the blade width in the meridional direction is defined by a line on said pressure surface and a line on said suction surface, each of said lines comprising a substantially straight line in a central portion which does not include a range corresponding to 20 to 40% of said blade height inwardly from said hub and tip end walls.

4. A turbine nozzle according to claim 3, wherein the distance from an intersection between the line on the pressure surface or the suction surface and said hub end wall to an intersection between an extension of said substantially straight line and said hub end wall, and the distance from an intersection between the line on the pressure surface or the suction surface and said tip end wall to an intersection between an extension of said substantially straight line and said tip end wall have a maximum value at the leading edge of said nozzle blade.

5. A turbine nozzle according to claim 4, wherein said maximum value ranges from 5 to 15% of said blade height.

6. A turbine nozzle according to claim 4, wherein said distances at said leading edge of said nozzle blade are in the range of 5 to 15% of said blade height, and are at least 4% of said blade height within a region from said leading edge of said nozzle blade to a position of at least 30% of the blade width in the meridional direction.