Gas turbine engine

Patent metadata

Field	Value
Publication number	US-11536161-B2
Application number	US-201916715376-A
Country	US
Kind code	B2
Filing date	Dec 16, 2019
Priority date	Jun 19, 2017
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

Abstract

A gas turbine engine including: an exhaust diffuser including an inner tube and an outer tube that form therebetween an annular exhaust passage; a bearing chamber formed radially inside the inner tube for accommodating a bearing that supports a rotor of a turbine; a plurality of hollow struts extending across the exhaust passage; an oil introduction passage extending through one of the struts for introducing oil to be supplied to the bearing chamber; an oil drain passage extending through one of the struts for draining the oil from an exhaust oil inlet opened on a bottom surface of the bearing chamber; and an oil discharge passage for discharging a portion of the oil having passed through the oil introduction passage toward the oil drain inlet.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a turbine;
a bearing configured to rotatably support a rotor of the turbine;
an exhaust diffuser connected to a downstream end of the turbine, the exhaust diffuser including an inner tube and an outer tube such that the inner tube and the outer tube form therebetween an exhaust passage having an annular shape;
a bearing chamber formed radially inside the inner tube and configured to accommodate the bearing;
a plurality of hollow struts extending across the exhaust passage and connecting the inner tube and the outer tube;
an oil introduction passage extending through first one of the plurality of the hollow struts and configured to introduce a first portion of oil to be supplied to the bearing chamber;
an oil drain passage extending through second one of the plurality of the hollow struts and configured to drain the oil from an oil drain inlet opened on a bottom surface of the bearing chamber; and
an oil discharge passage configured to discharge a second a portion of the oil having passed through the oil introduction passage directly to the oil drain inlet.

2. The gas turbine engine as claimed in claim 1 , wherein the oil discharge passage is configured to discharge the oil from an inside of the bearing chamber toward the oil drain inlet.

3. The gas turbine engine as claimed in claim 1 , wherein the oil discharge passage branches off at a position in the oil introduction passage, radially inside the first one of the plurality of the hollow struts.

4. The gas turbine engine as claimed in claim 3 , comprising:
an upper oil supply passage branching off from the oil introduction passage and configured to supply the oil from above the rotor into the bearing chamber; and
a lower oil supply passage branching off from the oil introduction passage and configured to supply the oil from below the rotor into the bearing chamber.

5. The gas turbine engine as claimed in claim 3 , wherein the rotor has a rear end located forward with respect to an axial position of the oil introduction passage, and the oil discharge passage extends along an axis of the oil introduction passage.

6. The gas turbine engine as claimed in claim 5 , wherein the oil introduction passage, the oil discharge passage and the oil drain passage extend in a vertical direction and are arranged concentrically with each other.

7. The gas turbine engine as claimed in claim 3 , wherein the rotor has a rear end located rearward with respect to an axial position of the oil introduction passage, and the oil discharge passage extends so as to bypass the rotor.

8. The gas turbine engine as claimed in claim 7 , wherein the rotor has a rotor cover that covers the rear end of the rotor, and at least a part of the oil discharge passage is formed inside the rotor cover.

9. The gas turbine engine as claimed in claim 1 , further comprising:
an upper oil supply passage branching off from the oil introduction passage and configured to supply the oil from above the rotor into the bearing chamber; and
a lower oil supply passage branching off from the oil introduction passage and configured to supply the oil from below the rotor into the bearing chamber, wherein
the oil discharge passage is provided so as to branch from the lower oil supply passage.

10. The gas turbine engine as claimed in claim 1 , wherein the oil discharge passage has a downstream end portion formed with an accelerating part configured to accelerate the oil.

11. The gas turbine engine as claimed in claim 10 , wherein the accelerating part has a shape with a gradually reduced diameter from an upstream side toward a downstream side.

12. The gas turbine engine as claimed in claim 10 , wherein the accelerating part is formed such that the accelerating part has a smaller channel cross-sectional area than that of an upstream side of the accelerating part and has a longer channel perimeter in a cross section than that of the upstream side of the accelerating part.

13. The gas turbine engine as claimed in claim 1 , wherein the oil drain passage has an upstream end portion formed with a throat part.

Assignees

• Kawasaki Heavy Ind Ltd

Inventors

• Ikeguchi Takuya
• Terauchi Koji
• Tanaka Mitsuaki
• Arisawa Hidenori
• Shinoda Yuji
• Noguchi Yoshiyuki

Classifications

• F01D25/166

  Sliding contact bearing (gas bearings F01D25/22) · CPC title

• F05D2260/98

  Lubrication · CPC title

• F01D25/183

  Sealing means · CPC title

• F01D25/18

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title