JPS5851028U - Aviation gas turbine engine lubricating oil air cooling system - Google Patents
Aviation gas turbine engine lubricating oil air cooling systemInfo
- Publication number
- JPS5851028U JPS5851028U JP14645781U JP14645781U JPS5851028U JP S5851028 U JPS5851028 U JP S5851028U JP 14645781 U JP14645781 U JP 14645781U JP 14645781 U JP14645781 U JP 14645781U JP S5851028 U JPS5851028 U JP S5851028U
- Authority
- JP
- Japan
- Prior art keywords
- lubricating oil
- cooling system
- gas turbine
- door
- air cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
第１図は従来の航空用ガス・タービン・エンジンの外装
型および内装型の潤滑油空冷装置の一例を示す断面図、
第２図は本考案のバイパス・ダクト外側に装着した外装
型の一実施例の構成を示す斜視図、第３図は第２図の空
気導入扉の閉の場合の作動状態を示すエンジン断面図、
第４図は第２図の空気導入扉の開の場合の作動状態を示
すエンジン断面図、第５図は本考案のバイパス・ダクト
内側に装着した内装型の別の実施例の構成を示す斜視図
、第６図は第５図の別の実施例の扉の閉の ゛場合の
作動状態図、第７図は第５図の別の実施例の扉の開の場
合の作動状態図である。
１：・・・・・冷却装置本体、２・・・・・・バイパス
・ダクト、３・・・・・・加圧空気の一部（冷却用空気
）、４・・・・・・空気導入穴、５・・・・・・空気導
入扉、５ａ、 ５ｂ・・・・・・扉、６・・・・・・
空気導入ダクト、７・・・・・・潤滑油、８・・・・・
・制御装置、９・・・・・・電気信号、１０・・・・・
・サーボ装置、 −１１・・・・・・高圧サーボ
燃料、Ｘ・・・・・・エンジン作動状態量、Ｙ・・・・
・・飛行環境条件、１０１・・・・・・外装型潤滑油空
冷装置、１０２・・・・・・内装型潤滑油空冷装置、１
０３・・・・・・空気導入穴。
竿２°凹
り
−「・FIG. 1 is a sectional view showing an example of a conventional external type and internal type lubricating oil air cooling system for an aircraft gas turbine engine;
Fig. 2 is a perspective view showing the configuration of an embodiment of the exterior type installed on the outside of the bypass duct of the present invention, and Fig. 3 is a sectional view of the engine showing the operating state when the air introduction door of Fig. 2 is closed. ,
Fig. 4 is a sectional view of the engine showing the operating state when the air introduction door in Fig. 2 is open, and Fig. 5 is a perspective view showing the configuration of another embodiment of the internal type installed inside the bypass duct of the present invention. Figure 6 is an operating state diagram of another embodiment shown in Fig. 5 when the door is closed, and Fig. 7 is an operating state diagram of another embodiment shown in Fig. 5 when the door is opened. . 1: ... Cooling device body, 2 ... Bypass duct, 3 ... Part of pressurized air (cooling air), 4 ... Air introduction Hole, 5...Air introduction door, 5a, 5b...Door, 6...
Air introduction duct, 7...Lubricating oil, 8...
・Control device, 9... Electric signal, 10...
・Servo device, -11... High pressure servo fuel, X... Engine operating state quantity, Y...
... Flight environment conditions, 101 ... External type lubricating oil air cooling system, 102 ... Internal type lubricating oil air cooling system, 1
03...Air introduction hole. Rod 2° concave - "・
Claims (1)
着され、ファンで加圧された空気の一部を冷却装置本体
に導入して潤滑油を冷却する航空用ガス・タービン・エ
ンジンの潤滑油空冷装置基どおいて、該冷却装置本体の
空気導入側に扉を開閉可能に設けるとともに該冷却装置
本体に該扉駆動用のサーボ装置を配設し、かつエンジン
作動状態量および飛行環境条件が入力している制御装置
から該扉開閉のための電気信号を該サーボ装置に送−る
よう構成したことを特徴とする航空用ガス・タービン・
エンジンの潤滑油空冷装置。A lubricating oil air cooling system unit for aviation gas turbine engines that is installed in the engine fan case or bypass φ duct and cools the lubricating oil by introducing a portion of the air pressurized by the fan into the cooling system body. A door is provided on the air introduction side of the cooling device main body so as to be openable and closable, and a servo device for driving the door is provided in the cooling device main body, and engine operating state quantities and flight environment conditions are input. An aviation gas turbine characterized in that the controller is configured to send electrical signals for opening and closing the door to the servo device.
Engine lubricating oil air cooling system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14645781U JPS5851028U (en) | 1981-10-01 | 1981-10-01 | Aviation gas turbine engine lubricating oil air cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14645781U JPS5851028U (en) | 1981-10-01 | 1981-10-01 | Aviation gas turbine engine lubricating oil air cooling system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5851028U true JPS5851028U (en) | 1983-04-06 |
| JPS6124675Y2 JPS6124675Y2 (en) | 1986-07-24 |
Family
ID=29939362
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14645781U Granted JPS5851028U (en) | 1981-10-01 | 1981-10-01 | Aviation gas turbine engine lubricating oil air cooling system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5851028U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007247651A (en) * | 2006-03-17 | 2007-09-27 | United Technol Corp <Utc> | Heat exchange system |
-
1981
- 1981-10-01 JP JP14645781U patent/JPS5851028U/en active Granted
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007247651A (en) * | 2006-03-17 | 2007-09-27 | United Technol Corp <Utc> | Heat exchange system |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6124675Y2 (en) | 1986-07-24 |
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