JPH0587655B2 - - Google Patents
Info
- Publication number
- JPH0587655B2 JPH0587655B2 JP10536589A JP10536589A JPH0587655B2 JP H0587655 B2 JPH0587655 B2 JP H0587655B2 JP 10536589 A JP10536589 A JP 10536589A JP 10536589 A JP10536589 A JP 10536589A JP H0587655 B2 JPH0587655 B2 JP H0587655B2
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- engine
- core engine
- fan
- combustor
- 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
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 238000010276 construction Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は、コアエンジン分離型ターボフアンエ
ンジンに関する。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a core engine separated turbofan engine.
（従来の技術）
ターボフアンエンジンは、良く知られる如く、
フアン、圧縮機、燃焼器及びタービンを順次ケー
ス内に配し、タービンとフアンをシヤフトで連結
した基本構造を有す。このターボフアンエンジン
は、フアンを通つた空気の一部はフアンにより加
速されて排出され、残りの空気が圧縮機で圧縮さ
れ、次いで、燃焼されて、タービンを回転させ
る。タービンの回転力は、フアンに伝達されてフ
アンの回転に利用される。タービンを通つた空気
は排気ガスとなつて、フアンを通つた空気と共に
排出させて推力を得ている。(Prior art) As is well known, the turbofan engine is
It has a basic structure in which a fan, compressor, combustor, and turbine are sequentially arranged inside a case, and the turbine and fan are connected by a shaft. In this turbofan engine, a part of the air passing through the fan is accelerated and discharged by the fan, and the remaining air is compressed by a compressor and then combusted to rotate a turbine. The rotational force of the turbine is transmitted to the fan and used to rotate the fan. The air that passes through the turbine becomes exhaust gas and is discharged along with the air that passes through the fan to generate thrust.
（本発明が解決しようとする課題）
現在使用されているターボフアンエンジンは、
フアンの軸心とタービンの軸心とを同一線上に配
していることから、フアンの推力方向に沿つてコ
アエンジンを設置する必要がある。このため、タ
ーボフアンエンジンの航空機への取付位置が限定
され、設計の自由度が小さい。さらに、従来のタ
ーボフアンエンジンは、垂直離着陸用として使用
しようとすると、水平飛行のための推力装置とし
て適さない欠点がある。(Problem to be solved by the present invention) The turbofan engine currently in use is
Since the axis of the fan and the axis of the turbine are arranged on the same line, it is necessary to install the core engine along the direction of thrust of the fan. Therefore, the mounting position of the turbofan engine on the aircraft is limited, and the degree of freedom in design is small. Furthermore, when conventional turbofan engines are used for vertical takeoff and landing, they have the disadvantage that they are not suitable as thrust devices for horizontal flight.
それ故に、本発明は、前述した従来技術の不具
合を解消させることを解決すべき課題とする。 Therefore, it is an object of the present invention to solve the above-mentioned problems of the prior art.
（課題を解決するための手段）
本発明は、前述した課題を解決するために、圧
縮機、該圧縮機を駆動するための燃焼器及びター
ビンを有する少くとも１つのコアエンジンと；該
コアエンジンから分離され、且つ該コアエンジン
からの高圧空気が供給されるフアン駆動用燃焼器
及びタービン、該タービンにより駆動されるフア
ンを有する少くとも１つの推進装置とを有するコ
アエンジン分離型ターボフアンエンジンを提供す
る。(Means for Solving the Problems) In order to solve the above-mentioned problems, the present invention provides at least one core engine having a compressor, a combustor for driving the compressor, and a turbine; A core engine separated type turbofan engine having a fan-driving combustor and a turbine separated from the core engine and supplied with high-pressure air from the core engine, and at least one propulsion device having a fan driven by the turbine. provide.
（作用）
本発明では、コアエンジンと推進装置とを別個
にし且つ両者を高圧空気ダクトを介して連結した
ことから、推進装置を所望の位置に配することを
可能とする。(Function) In the present invention, since the core engine and the propulsion device are separate and connected via a high-pressure air duct, it is possible to arrange the propulsion device at a desired position.
（実施例）
コアエンジン分離型ターボフアンエンジン１
は、コアエンジン２と、コアエンジン２とは分離
した推進装置３とからなる。コアエンジン２は、
ケース４内に、圧縮機５、燃焼器６及びタービン
７を有し、タービン７を圧縮機５にシヤフト８を
用いて連結する。コアエンジン２の個々の要素は
公知構成のものである。圧縮機５で圧縮された空
気は、その一部が燃焼器６及びタービン７に導入
され、タービン７による圧縮機５の駆動に用いら
れる。残りの高圧空気はダクト９に導入される。(Example) Core engine separated turbofan engine 1
consists of a core engine 2 and a propulsion device 3 separated from the core engine 2. Core engine 2 is
The case 4 includes a compressor 5, a combustor 6, and a turbine 7, and the turbine 7 is connected to the compressor 5 using a shaft 8. The individual elements of the core engine 2 are of known construction. A portion of the air compressed by the compressor 5 is introduced into the combustor 6 and the turbine 7, and is used by the turbine 7 to drive the compressor 5. The remaining high pressure air is introduced into duct 9.
推進装置３は、シユラウド１０内のフアン１
１、フアン１１と同心のケース１２内の燃焼器１
３とタービン１４を有し、ダクト９を燃焼器１３
に連結させる。推進装置３の個々の要素は、公知
構成のものを用いる。ダクト９を介して燃焼器１
３に入つた高圧空気は、燃焼空気として燃料を燃
焼させてタービン１４を駆動する。タービン１４
の回転トルクが、フアン１１を回転させ、推力を
作る。 The propulsion device 3 includes a fan 1 in the shroud 10.
1. Combustor 1 in case 12 concentric with fan 11
3 and a turbine 14, and the duct 9 is connected to a combustor 13.
Connect to. The individual elements of the propulsion device 3 are of known construction. Combustor 1 via duct 9
The high pressure air that has entered the turbine 3 burns fuel as combustion air and drives the turbine 14. Turbine 14
The rotating torque rotates the fan 11 and creates thrust.
第２図は、本発明のターボフアンエンジンの応
用例を示す。コアエンジン２を二基用い、コアエ
ンジン２からのダクト９を、高圧空気制御装置１
５に連結し、コアエンジン２から供給される高圧
空気の圧縮比（20−50の比）、圧力、流量、温度
等を制御してから、推進装置３へダクト９を介し
て供給する。勿論、高圧空気制御装置１５を介す
ることなく、直接推進装置３に高圧空気を送つて
もよい。又、コアエンジン２と推進装置３との数
は特定されない。 FIG. 2 shows an example of application of the turbofan engine of the present invention. Two core engines 2 are used, and the duct 9 from the core engines 2 is connected to the high pressure air control device 1.
5 and controls the compression ratio (ratio of 20-50), pressure, flow rate, temperature, etc. of the high-pressure air supplied from the core engine 2, and then supplies it to the propulsion device 3 via the duct 9. Of course, high-pressure air may be sent directly to the propulsion device 3 without going through the high-pressure air control device 15. Further, the number of core engines 2 and propulsion devices 3 is not specified.
第３図は、航空機への応用例を示す。コアエン
ジン２を胴体後部に３基づつ配置し、推進用フア
ンとしての推進装置３を２基、垂直離着陸用フア
ンとしての推進装置３を６基使用している。この
ように、推進装置３を、推力用及び離着陸用とし
て多用できる。 FIG. 3 shows an example of application to an aircraft. Three core engines 2 are arranged at the rear of the fuselage, two propulsion devices 3 are used as propulsion fans, and six propulsion devices 3 are used as vertical takeoff and landing fans. In this way, the propulsion device 3 can be used extensively for thrust and for takeoff and landing.
（効果）
本発明は、個々には従来構成の装置を用い、そ
の配列と組合せを変えたのみであるから、容易に
製作できる。(Effects) The present invention can be easily manufactured because it uses devices with conventional configurations and only changes their arrangement and combination.
第１図は本発明の一例の断面図、第２図は第１
応用例を示す正面図、第３図は第２応用例を示す
斜視図である。
図中：１……ターボフアンエンジン、２……コ
アエンジン、３……推進装置、４……ケース、５
……圧縮機、６，１３……燃焼器、７，１４……
タービン、８……シヤフト、９……ダクト、１１
……フアン。
FIG. 1 is a sectional view of an example of the present invention, and FIG. 2 is a cross-sectional view of an example of the present invention.
FIG. 3 is a front view showing an applied example, and FIG. 3 is a perspective view showing a second applied example. In the diagram: 1...Turbofan engine, 2...Core engine, 3...Propulsion device, 4...Case, 5
...Compressor, 6,13...Combustor, 7,14...
Turbine, 8... Shaft, 9... Duct, 11
...Juan.
Claims (1)
びタービンを有する少くとも１つのコアエンジン
と；該コアエンジンから分離され、且つ該コアエ
ンジンからの高圧空気が供給されるフアン駆動用
燃焼器及びタービン、該タービンにより駆動され
るフアンを有する少くとも１つの推進装置とを有
するコアエンジン分離型ターボフアンエンジン。 ２ 高圧空気の圧力比が２０−５０である請求項
１のコアエンジン分離型ターボフアンエンジン。 ３ 推進装置の少くとも一部が垂直離陸用に使用
される請求項１のコアエンジン圧縮型ターボフア
ンエンジン。[Claims] 1. At least one core engine having a compressor, a combustor for driving the compressor, and a turbine; separated from the core engine and supplied with high pressure air from the core engine; A separate core engine turbofan engine having a combustor and a turbine for driving a fan, and at least one propulsion device having a fan driven by the turbine. 2. The core engine separated turbofan engine according to claim 1, wherein the pressure ratio of the high pressure air is 20-50. 3. The core engine compression turbofan engine of claim 1, wherein at least a portion of the propulsion system is used for vertical takeoff.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10536589A JPH02283821A (en) | 1989-04-25 | 1989-04-25 | Core engine separating type turbo fan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10536589A JPH02283821A (en) | 1989-04-25 | 1989-04-25 | Core engine separating type turbo fan engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH02283821A JPH02283821A (en) | 1990-11-21 |
| JPH0587655B2 true JPH0587655B2 (en) | 1993-12-17 |
Family
ID=14405695
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10536589A Granted JPH02283821A (en) | 1989-04-25 | 1989-04-25 | Core engine separating type turbo fan engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH02283821A (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003137192A (en) | 2001-10-31 | 2003-05-14 | Mitsubishi Heavy Ind Ltd | Vertical taking-off/landing craft |
| JP2003206806A (en) * | 2002-01-16 | 2003-07-25 | National Aerospace Laboratory Of Japan | Turbo fan engine of core engine separation type |
| JP2003206746A (en) * | 2002-01-16 | 2003-07-25 | National Aerospace Laboratory Of Japan | Multi-fan type core engine separate type turbofan engine |
| EP1637725A3 (en) * | 2004-09-15 | 2009-04-01 | Munoz Saiz, Manuel | Turbofan or turbojet arrangements for vehicles craft, aircraft and the like |
| US7266940B2 (en) * | 2005-07-08 | 2007-09-11 | General Electric Company | Systems and methods for power generation with carbon dioxide isolation |
| WO2016009376A1 (en) * | 2014-07-18 | 2016-01-21 | Pegasus Universal Aerospace (Pty) Ltd. | Vertical take-off and landing aircraft |
| CN110529251A (en) * | 2019-08-22 | 2019-12-03 | 中国人民解放军陆军航空兵学院 | A kind of parallel combustion chambers turboaxle motor |
-
1989
- 1989-04-25 JP JP10536589A patent/JPH02283821A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPH02283821A (en) | 1990-11-21 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313111 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| EXPY | Cancellation because of completion of term |