Gas turbine engine

Patent metadata

Field	Value
Publication number	US-11713714-B2
Application number	US-202017770314-A
Country	US
Kind code	B2
Filing date	Oct 20, 2020
Priority date	Oct 21, 2019
Publication date	Aug 1, 2023
Grant date	Aug 1, 2023

Abstract

A gas turbine engine includes: a main passage through which compressed air extracted from a compressor is guided to a bearing; and an oil supply device that includes an oil tank storing oil and supplies the oil to the main passage through which the compressed air flows to generate oil mist. The oil supply device includes: a pressure reducer disposed at the main passage; a bypass passage that bypasses the pressure reducer and connects an upstream passage and a downstream passage; a holding chamber disposed at the bypass passage and having a predetermined volume; a switching mechanism that permits or blocks communication between the holding chamber and the oil tank, communication between the holding chamber and the upstream passage, and communication between the holding chamber and the downstream passage; and a controller that controls the switching mechanism.

First claim

The invention claimed is:

1. A gas turbine engine in which a compressor, a combustor, and a turbine are arranged so as to be lined up along a rotating shaft,
the gas turbine engine comprising:
a casing accommodating the compressor, the combustor, and the turbine;
a bearing arranged inside the casing;
a main passage through which compressed air extracted from the compressor is guided to the bearing; and
an oil supply device that includes an oil tank storing oil and supplies the oil to the main passage through which the compressed air flows to generate oil mist, wherein:
the oil supply device includes
a pressure reducer that is disposed at the main passage and makes pressure in a downstream passage of the main passage lower than pressure in an upstream passage of the main passage, the downstream passage being a portion located downstream of the pressure reducer, the upstream passage being a portion located upstream of the pressure reducer,
a bypass passage that bypasses the pressure reducer and connects the upstream passage and the downstream passage,
a holding chamber disposed at the bypass passage and having a predetermined volume,

a switching mechanism that permits or blocks communication between the holding chamber and the oil tank, communication between the holding chamber and the upstream passage, and communication between the holding chamber and the downstream passage, and
a controller that controls the switching mechanism; and
the controller controls the switching mechanism such that the switching mechanism switches to a first state, a second state, and a third state in this order,
the first state being a state where the communication between the holding chamber and the oil tank is blocked, the communication between the holding chamber and the upstream passage is blocked, and the communication between the holding chamber and the downstream passage is permitted,
the second state being a state where the communication between the holding chamber and the oil tank is permitted, the communication between the holding chamber and the upstream passage is blocked, and the communication between the holding chamber and the downstream passage is blocked,
the third state being a state where the communication between the holding chamber and the oil tank is blocked, the communication between the holding chamber and the upstream passage is permitted, and the communication between the holding chamber and the downstream passage is permitted.

2. The gas turbine engine according to claim 1 , wherein:
the oil tank includes
an oil chamber that stores the oil,
an air chamber that communicates with the main passage, and
a divider that separates the oil chamber from the air chamber and is movable such that a volume of the oil chamber decreases when a volume of the air chamber increases; and
the oil supply device further includes a tank inlet passage through which a part of the compressed air flowing through the upstream passage is guided to the air chamber.

3. The gas turbine engine according to claim 1 , wherein:
the switching mechanism includes
a first control valve that is disposed at the bypass passage and permits or blocks at least the communication between the holding chamber and the upstream passage and
a second control valve that is disposed at a portion of the bypass passage which portion is located downstream of the first control valve and permits or blocks at least the communication between the holding chamber and the downstream passage; and
the first control valve or the second control valve is a three-way valve that permits or blocks the communication between the holding chamber and the upstream passage or between the holding chamber and the downstream passage, and in addition, permits or blocks the communication between the holding chamber and the oil tank.

4. The gas turbine engine according to claim 3 , wherein:
the bypass passage is comprised of a pipe; and
the holding chamber is a portion of the pipe which portion is located between the first control valve and the second control valve.

5. The gas turbine engine according to claim 1 , wherein the pressure reducer is a check valve that prevents the compressed air from flowing from the downstream passage to the upstream passage.

Assignees

• Kawasaki Heavy Ind Ltd
• Kawasaki Jugkogyo Kk

Inventors

• Komori Shinsaku
• Fujii Takafumi
• Okuwa Tatsuya
• Maesato Hikaru

Classifications

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2260/98

  Lubrication · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F02C7/06 Primary

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F16N7/32

  Mist lubrication (splash lubrication F16N7/26) · CPC title