Air turbine drive spindle

Patent metadata

Field	Value
Publication number	US-11325140-B2
Application number	US-201716328510-A
Country	US
Kind code	B2
Filing date	Aug 8, 2017
Priority date	Aug 30, 2016
Publication date	May 10, 2022
Grant date	May 10, 2022

Abstract

An air turbine drive spindle capable of suppressing a pressure increase inside a through hole is provided. A spindle includes a rotary shaft and an outer circumferential member (a housing assembly, a cover and a nozzle plate). The rotary shaft is provided with a through hole. The outer circumferential member includes a bearing sleeve configured to surround at least a portion of an outer circumferential surface of the rotary shaft. The outer circumferential member includes a gas supply portion and a gas exhaust hole. The spindle includes a second gas exhaust portion (a first gas exhaust hole and a first gas flow passage). The second gas exhaust portion is independent of the gas exhaust hole and continuous to outside from a gas exhaust space.

First claim

The invention claimed is:

1. An air turbine drive spindle comprising:
a rotary shaft provided with a through hole, the rotary shaft including
a leading end portion,
a base end portion located opposite to the leading end portion, and
a plurality of rotor blades disposed at the base end portion along a rotation direction of the rotary shaft; and

an outer circumferential member including a bearing sleeve configured to surround at least a portion of an outer circumferential surface of the rotary shaft,
the outer circumferential member including
a gas supply portion configured to spray gas onto each of the plurality of rotor blades so as to rotate the rotary shaft, and
a first gas exhaust portion configured to discharge the gas sprayed onto each of the plurality of rotor blades from a gas exhaust space facing each of the plurality of rotor blades to outside of the outer circumferential member,

the gas exhaust space that faces the base end portion of the rotary shaft, and is continuous to the through hole of the rotary shaft,
the air turbine drive spindle further comprising a second gas exhaust portion that is independent of the first gas exhaust portion, the second gas exhaust portion including at least one gas exhaust hole penetrating through a portion of the rotary shaft to discharge the gas to the outside from the gas exhaust space,
wherein the at least one gas exhaust hole being formed in a surface of the rotary shaft that faces the gas exhaust space so that the gas flows in the at least one gas exhaust hole from the gas exhaust space.

2. The air turbine drive spindle according to claim 1 , wherein
the second gas exhaust portion includes
a gas flow passage extending through the outer circumferential member from a surface portion facing the at least one gas exhaust hole to a surface portion located adjacent to the leading end portion of the rotary shaft.

3. The air turbine drive spindle according to claim 2 , further comprising a sealing member disposed in a connection portion between the gas exhaust space and the through hole.

4. The air turbine drive spindle according to claim 1 , wherein the second gas exhaust portion includes a gas flow passage extending from a surface portion of the outer circumferential member that faces the gas exhaust space to a surface portion of the outer circumferential member located adjacent to the leading end portion of the rotary shaft.

5. The air turbine drive spindle according to claim 1 , wherein the second gas exhaust portion includes a gas flow passage extending from a surface portion of the outer circumferential member that faces the gas exhaust space to a surface portion of the outer circumferential member located in a radial direction intersecting with a direction in which the rotary shaft extends.

6. An air turbine drive spindle comprising:
a rotary shaft provided with a through hole, the rotary shaft including
a leading end portion,
a base end portion located opposite to the leading end portion, and
a plurality of rotor blades disposed at the base end portion along a rotation direction of the rotary shaft; and

an outer circumferential member including a bearing sleeve configured to surround at least a portion of an outer circumferential surface of the rotary shaft,
the outer circumferential member including
a gas supply portion configured to spray gas onto each of the plurality of rotor blades so as to rotate the rotary shaft, and
a first gas exhaust portion configured to discharge the gas sprayed onto each of the plurality of rotor blades from a gas exhaust space facing each of the plurality of rotor blades to outside of the outer circumferential member,

the gas exhaust space that faces the base end portion of the rotary shaft and is continuous to the through hole of the rotary shaft,
the air turbine drive spindle further comprising a second gas exhaust portion that is independent of the first gas exhaust portion, the second gas exhaust portion including at least one gas exhaust hole penetrating through a portion of the rotary shaft to discharge the gas to the outside from the gas exhaust space,
wherein the at least one gas exhaust hole is formed in an inner surface of the through hole of the rotary shaft so that the gas flows in the at least one gas exhaust hole from the gas exhaust space through the through hole.

7. The air turbine drive spindle according to claim 6 , wherein
the second gas exhaust portion includes
a gas flow passage extending through the outer circumferential member from a surface portion facing the at least one gas exhaust hole to a surface portion located adjacent to the leading end portion of the rotary shaft.

8. The air turbine drive spindle according to claim 7 , further comprising a sealing member disposed in a connection portion between the gas exhaust space and the through hole, wherein
the at least one gas exhaust hole is located closer to the leading end portion than the sealing member.

9. The air turbine drive spindle according to claim 6 , wherein the second gas exhaust portion includes a gas flow passage extending from a surface portion of the outer circumferential member that faces the gas exhaust space to a surface portion of the outer circumferential member located adjacent to the leading end portion of the rotary shaft.

10. The air turbine drive spindle according to claim 8 , wherein the second gas exhaust portion includes a gas flow passage extending from a surface portion of the outer circumferential member that faces the gas exhaust space to a surface portion of the outer circumferential member located in a radial direction intersecting with a direction in which the rotary shaft extends.

Assignees

• Ntn Toyo Bearing Co Ltd

Inventors

• Horiuchi Teruyoshi

Classifications

• B05B5/0415 Primary

  Driving means; Parts thereof, e.g. turbine, shaft, bearings · CPC title

• F01D1/02

  with stationary working-fluid guiding means and bladed or like rotor, {e.g. multi-bladed impulse steam turbines}(F01D1/24 takes precedence; without stationary working-fluid guiding means F01D1/18) · CPC title

• F01D15/06 Primary

  Adaptations for driving, or combinations with, hand-held tools or the like {control thereof} · CPC title

• F01D1/08 Primary

  having inward flow · CPC title

• B05B1/02

  designed to produce a jet, spray, or other discharge of particular shape or nature, e.g. in single drops, {or having an outlet of particular shape}(B05B1/26, B05B1/28, B05B1/34 take precedence) · CPC title