JP3364987B2 - Lubricating oil discharge mechanism of gas turbine engine - Google Patents
Lubricating oil discharge mechanism of gas turbine engineInfo
- Publication number
- JP3364987B2 JP3364987B2 JP14618193A JP14618193A JP3364987B2 JP 3364987 B2 JP3364987 B2 JP 3364987B2 JP 14618193 A JP14618193 A JP 14618193A JP 14618193 A JP14618193 A JP 14618193A JP 3364987 B2 JP3364987 B2 JP 3364987B2
- Authority
- JP
- Japan
- Prior art keywords
- lubricating oil
- discharge
- shaft
- power take
- gas turbine
- 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.)
- Expired - Lifetime
Links
Landscapes
- Lubrication Of Internal Combustion Engines (AREA)
Description
【発明の詳細な説明】
【０００１】
【産業上の利用分野】本発明は、ガスタービンエンジン
の潤滑油排出機構に関するものである。
【０００２】
【従来の技術】一般的なガスタービンエンジンの潤滑油
システムにおいては、油タンクから導かれる潤滑油は、
高圧圧縮機の駆動軸からパワーテイクオフシャフトによ
り駆動されるアクセサリギアボックスの歯車を介して駆
動される油ポンプにより加圧されて各部の軸受へ送給さ
れ、各部の軸受を潤滑したあと、主排出潤滑油管を通し
て排油ポンプにより回収されて油タンクへ戻されてい
る。
【０００３】また、図３に示すように、一部の潤滑油
（矢印Ａ）は、パワーテイクオフシャフト１の上部の軸
受２からパワーテイクオフシャフト１を取り囲むように
設けられた排出潤滑油管３内を落下して下部の軸受４を
通り、上下の各軸受２，４を潤滑したのちアクセサリギ
アボックス５へ入り、図示していない排油ポンプにより
回収されて油タンクへ戻されるように構成されている。
【０００４】
【発明が解決しようとする課題】前述のように、従来の
ガスタービンエンジンの潤滑油システムでは、軸受４を
潤滑した後に油タンクに回収されるべき戻りの潤滑油
（排出潤滑油）３は約１００℃でアクセサリギアボック
ス５の内部を通過するようになっている。
【０００５】通常、航空機用ガスタービンのアクセサリ
ギアボックス５のケーシング材料はアルミニウム合金、
歯車材料は歯面に焼入れ処理が施された鋼であり、これ
らの材料は１００℃程度の温度に対して、使用上特に問
題はない。
【０００６】しかし、マッハ数２以上の高速で巡航飛行
する航空機のようにエンジン全体が高温になる場合に
は、潤滑油温度を従来のエンジン並みに冷却することが
困難であり、２００℃以上となることもあり得る。
【０００７】このような場合、アクセサリギアボックス
５の材料の強度及び硬度が低下するという問題がある。
【０００８】本発明は、前述の実情に鑑み、排出潤滑油
をアクセサリギアボックスを通さずに油タンクへ回収し
得るガスタービンエンジンの潤滑油排出機構を提供する
ことを目的としてなしたものである。
【０００９】
【課題を解決するための手段】上記目的を達成するため
に、本発明のガスタービンエンジンの潤滑油排出機構で
は、パワーテイクオフシャフトを取り囲むようにアクセ
サリギヤボックスから上方へ突出し且つパワーテイクオ
フシャフトに平行な排出潤滑油管の下端部に、排出潤滑
油管の内周面からパワーテイクオフシャフトの回転方向
へ延びる接線に沿って外部へ貫通する吐出口を形成し、
該吐出口よりも下方に位置し且つ周縁部分が排出潤滑油
管の内周面に対して微小な空隙を隔てる円板状体をパワ
ーテイクオフシャフトに設け、前記排出潤滑油管の上部
を排出潤滑油が流入し得るように形成し、前記吐出口を
排油ポンプを介して油タンクに接続した構成とする。
【００１０】
【作用】本発明のガスタービンエンジンの潤滑油排出機
構においては、排出潤滑油管の内部でパワーテイクオフ
シャフトとともに回転している円板状体が、排出潤滑油
管内を流下し且つ円板状体の面状に衝突する排出潤滑油
に遠心力を付加し、この排出潤滑油を、排出潤滑油管の
下部内周面に沿って流動させたうえ、排出潤滑油管の内
周面から外部へ貫通する吐出口へ導き、排油ポンプによ
り油タンクへ回収する。
【００１１】
【実施例】以下、本発明の実施例を図面を参照しつつ説
明する。
【００１２】図１及び図２は、本発明のガスタービンエ
ンジンの潤滑油排出機構の一実施例の概略を表す断面図
であり、図中、図３と同じものには同じ符号を附けてあ
る。
【００１３】本発明のガスタービンエンジンの潤滑油排
出機構では、パワーテイクオフシャフト１を取り囲み且
つ該パワーテイクオフシャフトに平行する方向へ延びる
排出潤滑油管６は、下部に内周面の接線方向へ貫通する
吐出口７を備えており、また前記のパワーテイクオフシ
ャフト１は、前記吐出口７の下方に位置するスクロール
８を備えている。
【００１４】そして、前記排出潤滑油管６の上部に排出
潤滑油（矢印Ａ）が流入し得るように形成し、且つ該排
出潤滑油管６の前記吐出口７を図示していない排油ポン
プを介して油タンクに接続する。
【００１５】パワーテイクオフシャフト１に備えられた
スクロール８は、パワーテイクオフシャフト１とともに
回転し、排出潤滑油管６の上部から流入し排出潤滑油管
６内を落下してスクロール８に衝突する排出潤滑油（矢
印Ａ）に対して遠心力を付加し、遠心力を付加された該
排出潤滑油（矢印Ａ）は、排出潤滑油管６の下部の内周
面に沿って流動して吐出口７から流出し、図示していな
い排油ポンプにより油タンクに回収される。
【００１６】前記によれば、パワーテイクオフシャフト
１を取り囲むように設けた排出潤滑油管６の下部に吐出
口７を設け、該吐出口７の下方位置にパワーテイクオフ
シャフト１ともに回転するように設けたスクロール８に
より、該スクロール８に衝突する排出潤滑油（矢印Ａ）
に対して遠心力を付加し、該排出潤滑油（矢印Ａ）が前
記吐出口７から流出するように構成したので、排出潤滑
油（矢印Ａ）がアクセサリギアボックス５を経由して排
出されないため、排出潤滑油（矢印Ａ）の高温度に起因
するアクセサリギアボックス５の材料強度及び硬さの低
下を防ぐことができる。
【００１７】なお、前述の実施例では、排出潤滑油管６
の下部の吐出口７付近にパワーテイクオフシャフト１と
ともに回転するスクロール８を設けた場合について説明
したが、該スクロール８に代えてインペラを設けてもよ
いこと、その他、本発明の要旨を逸脱しない範囲内にお
いて種々変更を加え得ることは勿論である。
【００１８】
【発明の効果】本発明のガスタービンエンジンの潤滑油
排出機構によれば、パワーテイクオフシャフトとともに
回転するように設けた円板状体により、該円板状体に衝
突する排出潤滑油に対して遠心力を付加し、当該排出潤
滑油を、排出潤滑油管の内周面からパワーテイクオフシ
ャフトの回転方向へ延びる接線に沿って外部へ貫通する
吐出口から流出させる構成としたので、排出潤滑油がア
クセサリギヤボックスを経由して排出されず、これによ
り、高温の排出潤滑油に起因するアクセサリギヤボック
スの材料強度及び硬度の低下を防ぐことができるという
優れた効果を奏し得る。Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a lubricating oil discharging mechanism for a gas turbine engine. [0002] In a typical gas turbine engine lubricating oil system, lubricating oil guided from an oil tank is
After being pressurized by an oil pump driven from the drive shaft of the high-pressure compressor through the gears of an accessory gear box driven by a power take-off shaft and fed to the bearings of each part, after lubricating the bearings of each part, the main discharge The oil is recovered by the oil drain pump through the lubricating oil pipe and returned to the oil tank. As shown in FIG. 3, a part of the lubricating oil (arrow A) flows from an upper bearing 2 of the power take-off shaft 1 to a discharge lubricating oil pipe 3 provided to surround the power take-off shaft 1. After falling and passing through the lower bearing 4 and lubricating the upper and lower bearings 2 and 4, the lubricating oil enters the accessory gear box 5, is collected by a drain pump (not shown), and is returned to the oil tank. . As described above, in the conventional lubricating oil system for a gas turbine engine, return lubricating oil (discharge lubricating oil) to be collected in an oil tank after lubricating the bearing 4. 3 is designed to pass through the interior of the accessory gearbox 5 at about 100 ° C. [0005] Normally, the casing material of the accessory gearbox 5 of an aircraft gas turbine is made of aluminum alloy,
The gear material is steel whose teeth have been quenched, and these materials have no particular problem in use at temperatures of about 100 ° C. However, when the engine as a whole is hot, such as an aircraft cruising at a high speed of Mach number 2 or more, it is difficult to cool the lubricating oil temperature to the same level as a conventional engine. It can be. In such a case, there is a problem that the strength and hardness of the material of the accessory gear box 5 is reduced. The present invention has been made in view of the above circumstances, and has as its object to provide a lubricating oil discharging mechanism for a gas turbine engine that can collect discharged lubricating oil into an oil tank without passing through an accessory gear box. . [0009] In order to achieve the above object,
In the lubricating oil discharging mechanism of the gas turbine engine of the present invention,
Is, access to surrounding the power take-off shaft
Power take-off that projects upward from the sari gear box
Discharge lubrication at the lower end of the discharge lubrication oil pipe parallel to the shaft.
The direction of rotation of the power take-off shaft from the inner peripheral surface of the oil pipe
Forming a discharge port that penetrates to the outside along a tangent line extending to
The lubricating oil is located below the discharge port and has a peripheral portion
Power a disc-shaped body that separates a minute gap from the inner circumferential surface of the pipe.
Over take-off is provided on the shaft, the upper discharge the lubricating oil tube formed to discharge the lubricating oil may flow, a configuration that connects the discharge port to the oil tank via the oil discharge pump. The lubricating oil discharging device for a gas turbine engine according to the present invention.
Power take-off inside the discharge lubricating oil pipe
The disk that rotates with the shaft is
Discharged lubricating oil flowing down the pipe and colliding with the surface of the disk
Centrifugal force is applied to the exhaust lubricating oil pipe
After flowing along the lower inner peripheral surface,
Guide to the discharge port that penetrates from the peripheral surface to the outside, and
To the oil tank. Embodiments of the present invention will be described below with reference to the drawings. FIGS. 1 and 2 are cross-sectional views schematically showing an embodiment of a lubricating oil discharging mechanism for a gas turbine engine according to the present invention, in which the same components as those in FIG. 3 are denoted by the same reference numerals. . In the lubricating oil discharging mechanism for a gas turbine engine according to the present invention, a discharging lubricating oil pipe 6 surrounding the power take-off shaft 1 and extending in a direction parallel to the power take-off shaft penetrates a lower portion in a tangential direction of the inner peripheral surface. The power take-off shaft 1 includes a discharge port 7 and a scroll 8 located below the discharge port 7. A discharge lubricating oil (arrow A) is formed so as to be able to flow into the upper portion of the discharge lubricating oil pipe 6, and the discharge port 7 of the discharge lubricating oil pipe 6 is connected to a drain oil pump (not shown). To the oil tank. The scroll 8 provided on the power take-off shaft 1 rotates together with the power take-off shaft 1, flows in from the upper part of the discharge lubricating oil pipe 6, falls down in the discharge lubricating oil pipe 6, and collides with the discharged lubricating oil ( Centrifugal force is applied to the arrow A), and the discharged lubricating oil (arrow A) to which the centrifugal force is applied flows along the inner peripheral surface at the lower part of the drain lubricating oil pipe 6 and flows out from the discharge port 7. Is collected in an oil tank by a drain pump (not shown). According to the above, the discharge port 7 is provided below the discharge lubricating oil pipe 6 provided so as to surround the power take-off shaft 1, and the power take-off shaft 1 is provided at a position below the discharge port 7 so as to rotate together with the power take-off shaft 1. The discharged lubricating oil colliding with the scroll 8 by the scroll 8 (arrow A)
, And the discharged lubricating oil (arrow A) is configured to flow out of the discharge port 7. Therefore, the discharged lubricating oil (arrow A) is not discharged through the accessory gear box 5. In addition, it is possible to prevent the material strength and hardness of the accessory gear box 5 from decreasing due to the high temperature of the discharged lubricating oil (arrow A). In the above-described embodiment, the discharge lubricating oil pipe 6
A case has been described in which a scroll 8 that rotates together with the power take-off shaft 1 is provided in the vicinity of the discharge port 7 in the lower part of the drawing. However, an impeller may be provided instead of the scroll 8, and the scope of the present invention is not deviated. It is needless to say that various changes can be made within. According to the lubricating oil discharging mechanism of the gas turbine engine of the present invention, the discharged lubricating oil colliding with the disk-shaped body is provided by the disk-shaped body provided to rotate together with the power take-off shaft. adding a centrifugal force to, the discharge Jun
Lubricate the power take-off system from the inner peripheral surface of the discharge lubricating oil pipe.
Penetrates outward along a tangent extending in the direction of shaft rotation
Since the lubricating oil is discharged from the discharge port , the discharged lubricating oil is not discharged through the accessory gear box .
Therefore, it is possible to achieve an excellent effect that it is possible to prevent a decrease in the material strength and hardness of the accessory gear box caused by the high-temperature discharged lubricating oil.
【図面の簡単な説明】
【図１】本発明のガスタービンエンジンの潤滑油排出機
構の一実施例の概略を表す断面図である。
【図２】図１のＩＩ−ＩＩ矢視図である。
【図３】従来のガスタービンエンジンの潤滑油排出機構
の一例の概略を表す断面図である。
【符号の説明】
１ パワーテイクオフシャフト５ アクセサリギヤボックス
６ 排出潤滑油管
７ 吐出口
８ スクロール（円板状体）BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a sectional view schematically showing an embodiment of a lubricating oil discharging mechanism for a gas turbine engine according to the present invention. FIG. 2 is a view taken in the direction of arrows II-II in FIG. FIG. 3 is a cross-sectional view schematically illustrating an example of a conventional lubricating oil discharging mechanism of a gas turbine engine. [Description of Signs] 1 Power take-off shaft 5 Accessory gear box 6 Discharge lubricating oil pipe 7 Discharge port 8 Scroll (disk)
フロントページの続き (58)調査した分野(Int.Cl.7，ＤＢ名) F02C 1/00 - 9/58 F01M 1/00 - 9/12 Continuation of front page (58) Field surveyed (Int.Cl. 7 , DB name) F02C 1/00-9/58 F01M 1/00-9/12
Claims (1)
うにアクセサリギヤボックスから上方へ突出し且つパワ
ーテイクオフシャフトに平行な排出潤滑油管の下端部
に、排出潤滑油管の内周面からパワーテイクオフシャフ
トの回転方向へ延びる接線に沿って外部へ貫通する吐出
口を形成し、該吐出口よりも下方に位置し且つ周縁部分
が排出潤滑油管の内周面に対して微小な空隙を隔てる円
板状体をパワーテイクオフシャフトに設け、前記排出潤
滑油管の上部を排出潤滑油が流入し得るように形成し、
前記吐出口を排油ポンプを介して油タンクに接続したこ
とを特徴とするガスタービンエンジンの潤滑油排出機
構。(57) [Claims 1] surrounding the power take-off shaft
Protrude upward from the accessory gearbox and
-The lower end of the discharge lubricating oil pipe parallel to the take-off shaft
Power take-off shuffle from the inner peripheral surface of
Discharge to the outside along a tangent extending in the direction of rotation
Forming a port, located below the discharge port and having a peripheral portion
Is a circle that separates a minute gap from the inner peripheral surface of the drain lubricating oil pipe
A plate-shaped body is provided on the power take-off shaft, and an upper portion of the discharge lubricating oil pipe is formed so that the discharged lubricating oil can flow therein,
A lubricating oil discharging mechanism for a gas turbine engine, wherein the discharge port is connected to an oil tank via a drain pump.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14618193A JP3364987B2 (en) | 1993-06-17 | 1993-06-17 | Lubricating oil discharge mechanism of gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14618193A JP3364987B2 (en) | 1993-06-17 | 1993-06-17 | Lubricating oil discharge mechanism of gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH074262A JPH074262A (en) | 1995-01-10 |
| JP3364987B2 true JP3364987B2 (en) | 2003-01-08 |
Family
ID=15401972
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14618193A Expired - Lifetime JP3364987B2 (en) | 1993-06-17 | 1993-06-17 | Lubricating oil discharge mechanism of gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3364987B2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7055303B2 (en) * | 2003-12-22 | 2006-06-06 | Pratt & Whitney Canada Corp. | Gas turbine engine architecture |
| JP2007224860A (en) * | 2006-02-24 | 2007-09-06 | Honda Motor Co Ltd | Oil passage structure of internal combustion engine |
| FR2921973B1 (en) * | 2007-10-04 | 2011-04-29 | Snecma | INTERMEDIATE CASING OF TURBOJET AND TURBOREACTOR |
-
1993
- 1993-06-17 JP JP14618193A patent/JP3364987B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH074262A (en) | 1995-01-10 |
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