Radial turbine

• US 10,072,513 B2
• Filed: 11/14/2012
• Issued: 09/11/2018
• Est. Priority Date: 11/30/2011
• Status: Active Grant

• Current Assignee: Mitsubishi Heavy Industries, Ltd.
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Osako, Katsuyuki, Yokoyama, Takao, Jinnai, Yasuaki, Shiraishi, Takashi
• Primary Examiner(s): Shanske, Jason
• Assistant Examiner(s): Corday, Cameron
• Application Number:
  US14/360,846
• Publication Number:
  US 20140341729A1
• Time in Patent Office: 2,127 Days
• CPC Class Codes: F01D 17/165 for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F02B 37/24 by using pumps or turbines with adjustable guide vanes
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

A radial turbine comprises a plurality of nozzle vanes disposed along a circumferential direction inside a spiral scroll and configured to regulate a flow of a working gas from the scroll to a rotor blade, wherein each of the nozzle vane includes a leading edge bulging portion on both end portions in a width direction of an inlet leading edge portion, the leading edge bulging portion being bulged toward a pressure face side of the nozzle vane relative to a central portion, so that a vane angle is configured to correspond with an inflow angle of the working gas to be flown into the nozzle vane, and wherein each of the nozzle vane includes a trailing edge bulging portion on both end portions in a width direction of an outlet trailing edge portion, the trailing edge bulging portion being bulged toward the pressure face side relative to a central portion, so that an outflow angle of the working gas from the outlet trailing edge of the nozzle vane becomes uniform.

Claims

1. A radial turbine comprising a plurality of nozzle vanes disposed along a circumferential direction inside a spiral scroll and configured to regulate a flow of a working gas from the scroll to a rotor blade of a turbine rotor, each of said plurality of nozzle vanes being configured to be rotatable around a support axis mounted to a body of the nozzle vane as a rotational axis,

wherein each of the plurality of nozzle vanes includes,

an inlet leading edge portion;

an outlet trailing edge portion;

a leading edge central portion formed on a central portion in a width direction of the inlet leading edge portion, the leading edge central portion having two end portions;

a leading edge bulging portion formed on both end portions on an end side of the leading edge central portion in the width direction of the inlet leading edge portion, the leading edge bulging portion being bulged toward an outer surface side of the nozzle vane relative to the leading edge central portion;

a trailing edge central portion formed on a central portions in a width direction of the outlet trailing edge portion, the trailing edge central portion having two end portions; and

a trailing edge bulging portion formed on both end portions on an end side of the trailing edge central portion in the width direction of the outlet trailing edge portion, the trailing edge bulging portion being bulged toward the outer surface side of the nozzle vane relative to the trailing edge central portion,

wherein a width of the leading edge bulging portion is set to be within a range of from 15 to 20% relative to an entire width of the nozzle vane, and

wherein a width of the trailing edge bulging portion is set to be within the range of from 15 to 20% relative to the entire width of the nozzle vane.

2. The radial turbine according to claim 1, wherein the leading edge bulging portion is positioned further up on an upstream side in a length direction of the nozzle vane than the leading edge central portion.

3. The radial turbine according to claim 2, wherein each of the plurality of nozzle vanes is a variable nozzle vane supported rotatably around an intermediate portion of the nozzle vane in a length direction as a center of rotation, and the radial turbine is configured so that the leading edge bulging portion of one of two adjacent nozzle vanes among the nozzle vanes, and the trailing edge bulging portion of the other of the two adjacent nozzle vanes are close to each other when the nozzle vanes are in a totally-closed state.

4. The radial turbine according to claim 1, wherein

each of the plurality of nozzle vanes is a variable nozzle vane supported rotatably around an intermediate portion of the nozzle vane in a length direction as a center of rotation, and

a gap formed between a sidewall within an annular region of the spiral scroll and a portion of an end surface of the nozzle vane corresponding to the intermediate portion, is narrower than a gap formed between those portions of the end surface of the nozzle vane other than the intermediate portion and the sidewall outside the annular region, and

wherein the annular region is a region where a throat is formed by adjacent nozzle vanes when an opening degree of the nozzle vanes is within a range of from a middle opening degree to a small opening degree.

5. The radial turbine according to claim 1, wherein a vane angle of the leading edge bulging portion is larger than a vane angle of the leading edge central portion by a range of from 2 degrees to 13 degrees.

6. The radial turbine according to claim 1, wherein the a vane angle of the trailing edge bulging portion is larger than a vane angle of the trailing edge central portion by a range of from 2 degrees to 8 degrees.

7. A plurality of nozzle vanes disposed along a circumferential direction inside a spiral scroll and configured to regulate a flow of a working gas from the scroll to a rotor blade of a turbine rotor, each of said plurality of nozzle vanes being configured to be rotatable around a support axis mounted to a body of the nozzle vane as a rotational axis,

wherein each of the plurality of nozzle vanes includes,

an inlet leading edge portion;

an outlet trailing edge portion;

a leading edge central portion formed on a central portion in a width direction of the inlet leading edge portion, the leading edge central portion having two end portions;

a leading edge bulging portion formed on both end portions on an end side of the leading edge central portion in a width direction of the inlet edge portion, the leading edge bulging portion being bulged toward an outer surface of the nozzle vane relative to the leading edge central portion;

a trailing edge central portion formed on a central portion in a width direction of the outlet trailing edge portion, the trailing edge central portion having two end portions; and

a trailing edge bulging portion formed on both end portions on a side of the trailing edge central portion in the width direction of the outlet trailing edge portion, the trailing edge bulging portion being bulged toward the outer surface side of the nozzle vane relative to the trailing edge central portion, wherein

a width of the leading edge bulging portion is set to be within a range of from 15 to 20% relative to an entire width of the nozzle vane, and

a width of the trailing edge bulging portion is set to be within a range of from 15 to 20% relative to an entire width of the nozzle vane.