Rotor disc, rotor shaft, turbine rotor, and gas turbine

Patent metadata

Field	Value
Publication number	US-11982202-B2
Application number	US-202017604920-A
Country	US
Kind code	B2
Filing date	Apr 23, 2020
Priority date	May 24, 2019
Publication date	May 14, 2024
Grant date	May 14, 2024

Abstract

A rotor disc has diametrically outer surfaces, a diametrically inner surface, a plurality of blade root grooves recessed diametrically inward from the diametrically outer surfaces and aligned in a circumferential direction, and a plurality of hole groups formed in each of the plurality of blade root grooves and aligned in the circumferential direction. Each of the plurality of hole groups has a hole including a cooling orifice penetrating from the diametrically inner surface through to the diametrically outer surface. The width of each of the plurality of hole groups in the circumferential direction is greater than the width of each of the plurality of hole groups in an axial direction and smaller than a minimum gap among gaps between the plurality of hole groups in the circumferential direction.

First claim

The invention claimed is:

1. A rotor disc comprising:
a first diameter portion having a substantially columnar shape around an axis;
a second diameter portion having a substantially columnar shape around the axis; and
an upstream extension portion extending from an axial upstream side of the second diameter portion toward an axial upstream direction,
wherein a radius of the first diameter portion is larger than a radius of the second diameter portion,
wherein the second diameter portion is provided on an axial upstream side of the first diameter portion,
wherein the first diameter portion includes:
a first outer peripheral surface facing outward and away from the axis in a radial direction with respect to the axis; and
a plurality of blade root grooves which are recessed radially inward from the first outer peripheral surface, and which are arranged in a circumferential direction with respect to the axis,

wherein the second diameter portion includes:
a second outer peripheral surface facing outward and away from the axis in the radial direction;
a front surface facing in the axial upstream direction, the upstream extension portion extending from the front surface;
a plurality of communication grooves which are recessed radially inward from the second outer peripheral surface, each communication groove of the plurality of communication grooves including a communication groove bottom surface which faces radially outward;

an annular groove recessed from the front surface in an axial downstream direction, the annular groove extending in the circumferential direction with respect to the axis and including an inner groove side surface which faces radially outward; and
a plurality of channel groups formed for the plurality of blade root grooves, respectively, and arranged in the circumferential direction,

wherein the upstream extension portion has a radial inner surface which faces inward in the radial direction, and which is located radially inward of the communication groove bottom surface and the inner groove side surface,
wherein each channel group of the plurality of channel groups includes a plurality of channels which are recessed radially outward from the radial inner surface and which are arranged in the circumferential direction,
wherein at least one of the plurality of channels is a cooling channel penetrating from the radial inner surface to the communication groove bottom surface or the inner groove side surface,
wherein for each channel group of the plurality of channel groups, an outermost width of the plurality of channels of the channel group in the circumferential direction is larger than a width of the plurality of channels of the channel group in an axial direction in which the axis extends, and is smaller than a minimum interval of intervals between adjacent channel groups of the plurality of channel groups in the circumferential direction,
wherein each cooling channel communicates with a respective blade root groove of the plurality of blade root grooves, and
wherein for each channel group of the plurality of channel groups, an entirety of each channel of the plurality of channels of the channel group is arranged within the second diameter portion.

2. The rotor disc according to claim 1 ,
wherein for each channel group of the plurality of channel groups, a maximum channel interval of intervals between the plurality of channels of the channel group in the circumferential direction is smaller than the minimum interval of the intervals between adjacent channel groups of the plurality of channel groups in the circumferential direction.

3. The rotor disc according to claim 1 ,
wherein for each channel group of the plurality of channel groups, all of the channels of the plurality of channels of the channel group are the cooling channels.

4. The rotor disc according to claim 1 ,
wherein a position of an opening of the cooling channel on the communication groove bottom surface or the inner groove side surface in the circumferential direction is in a region in the circumferential direction in which a groove bottom surface of each of the plurality of the blade root grooves is present.

5. The rotor disc according to claim 1 ,
wherein a region of the radial inner surface around an opening of each channel of the plurality of channels of each of the plurality of channel groups on the radial inner surface is perpendicular to a direction in which the channel extends on a virtual plane including the axis and the channel.

6. A rotor shaft comprising:
a plurality of the rotor discs according to claim 1 ; and
a spindle bolt penetrating through the plurality of rotor discs in the axial direction to connect the plurality of rotor discs to each other, the rotor discs being arranged in the axial direction.

7. A turbine rotor comprising:
the rotor shaft according to claim 6 ; and
a plurality of rotor blades mounted in the plurality of blade root grooves, respectively, of each of the plurality of rotor discs.

8. A gas turbine comprising:
the turbine rotor according to claim 7 ; and
a turbine casing covering an outer periphery of the turbine rotor.

Assignees

• Mitsubishi Power Ltd
• Mitsubishi Heavy Ind Ltd

Inventors

• Kitagawa Kazuki
• Hashimoto Shinya

Classifications

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D5/06

  Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections {(F01D5/022, F01D5/023 take precedence)} · CPC title

• F01D5/066

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2220/32

  in gas turbines · CPC title