CN106677901A - Aeroengine - Google Patents
Aeroengine Download PDFInfo
- Publication number
- CN106677901A CN106677901A CN201610902862.2A CN201610902862A CN106677901A CN 106677901 A CN106677901 A CN 106677901A CN 201610902862 A CN201610902862 A CN 201610902862A CN 106677901 A CN106677901 A CN 106677901A
- Authority
- CN
- China
- Prior art keywords
- turbine
- jet pipe
- combustion chamber
- working medium
- engine
- 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.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
Abstract
The invention discloses an aeroengine. The aeroengine comprises a gas compressor, a combustion chamber, a turbine, a nozzle pipe, an auxiliary combustion chamber and an auxiliary nozzle pipe, wherein the gas compressor communicates with the turbine through the combustion chamber; a working medium outlet of the turbine communicates with the nozzle pipe; a working medium leading-out opening is formed in a fluid channel between the gas compressor and the turbine; and the working medium leading-out opening communicates with the auxiliary nozzle pipe through the auxiliary combustion chamber. The aeroengine disclosed by the invention is simple in structure and high in thrust efficiency.
Description
Technical field
The present invention relates to heat energy and dynamic field, more particularly to aero-engine.
Background technology
Traditional aero-engine (particularly ordnance engine) is reinforced although there is the technical scheme of after-burner
Combustion chamber is arranged on after turbine, therefore pressure ratio is relatively low, and thrust efficiency is necessarily relatively low.Accordingly, it would be desirable to invent a kind of new boat
Empty engine.
The content of the invention
In order to solve the above problems, technical scheme proposed by the present invention is as follows：
A kind of aero-engine of the present invention, including compressor, combustion chamber, turbine, jet pipe, subsidiary combustion room and attached spray
Pipe, combustion chamber described in the compressor Jing connects with the turbine, and the sender property outlet of the turbine is connected with the jet pipe, in institute
State and working medium export mouth is set on the fluid passage between compressor and the turbine, subsidiary combustion room described in the working medium export mouth Jing
Connect with the attached jet pipe.
Further optionally, arrange the subsidiary combustion room and combustion chamber suit.
A kind of aero-engine of the present invention, including compressor, combustion chamber, turbine, jet pipe and attached jet pipe, it is described to calm the anger
Combustion chamber connects with the turbine described in machine Jing, and the sender property outlet of the turbine is connected with the jet pipe, on the combustion chamber
If working medium export mouth, the working medium export mouth is connected with the attached jet pipe.
Further optionally, arrange the attached jet pipe and jet pipe suit.
In the present invention, so-called " combustion chamber " and " subsidiary combustion room " is combustion chamber, and title difference is intended merely to distinguish
And defined.
In the present invention, so-called " jet pipe " and " attached jet pipe " is jet pipe, title difference be intended merely to distinguish and in addition
Definition.
In the present invention, necessary part, list should be arranged where necessity according to heat energy and the known technology of dynamic field
Unit or system etc..
Beneficial effects of the present invention are as follows:Aero-engine simple structure disclosed by the invention, thrust efficiency is higher.
Description of the drawings：
Fig. 1：The structural representation of the embodiment of the present invention 1：
Fig. 2：The structural representation of the embodiment of the present invention 2.
Specific embodiment
Embodiment 1
A kind of aero-engine, as shown in figure 1, including compressor 1, combustion chamber 2, turbine 3, jet pipe 4, subsidiary combustion room 5
With attached jet pipe 6, combustion chamber 2 described in the Jing of the compressor 1 connects with the turbine 3, the sender property outlet of the turbine 3 with it is described
Jet pipe 4 is connected, and working medium export mouth, the working medium export mouth are set on the fluid passage between the compressor 1 and the turbine 3
Subsidiary combustion room 5 described in Jing connects with the attached jet pipe 6.
Used as disposable embodiment, the embodiment of the present invention 1 further can optionally select to make the subsidiary combustion
Room 5 and the suit of the combustion chamber 2 are arranged or non-suit is arranged.
Embodiment 2
A kind of aero-engine, as shown in Fig. 2 including compressor 1, combustion chamber 2, turbine 3, jet pipe 4 and attached jet pipe 6,
Combustion chamber 2 described in the Jing of the compressor 1 connects with the turbine 3, and the sender property outlet of the turbine 3 is connected with the jet pipe 4,
Working medium export mouth is set on the combustion chamber 2, the working medium export mouth is connected with the attached jet pipe 6.
Used as disposable embodiment, Example 1 and Example 2 of the present invention and its disposable embodiment can enter
One step optionally selects to arrange the jet pipe 4 and the attached jet pipe 6 suit or non-suit setting.
It is clear that the invention is not restricted to above example, according to techniques known and technology disclosed in this invention
Scheme, can derive or association goes out many flexible programs, and all these flexible programs also are regarded as the protection model for being the present invention
Enclose.
Claims (4)
1. a kind of aero-engine, including compressor (1), combustion chamber (2), turbine (3), jet pipe (4), subsidiary combustion room (5) and
Attached jet pipe (6), it is characterised in that：Combustion chamber (2) described in compressor (1) Jing connects with the turbine (3), the turbine
(3) sender property outlet is connected with the jet pipe (4), is set on the fluid passage between the compressor (1) and the turbine (3)
Working medium export mouth, subsidiary combustion room (5) described in the working medium export mouth Jing connect with the attached jet pipe (6).
2. aero-engine as claimed in claim 1, it is characterised in that：The subsidiary combustion room (5) and the combustion chamber (2) cover
Installing is put.
3. a kind of aero-engine, including compressor (1), combustion chamber (2), turbine (3), jet pipe (4) and attached jet pipe (6), its
It is characterised by：Combustion chamber (2) described in compressor (1) Jing connects with the turbine (3), the sender property outlet of the turbine (3)
Connect with the jet pipe (4), working medium export mouth, the working medium export mouth and the attached jet pipe are set on the combustion chamber (2)
(6) connect.
4. the aero-engine as any one of claims 1 to 3, it is characterised in that：The attached jet pipe (6) and the spray
Pipe (4) suit is arranged.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510762944 | 2015-11-10 | ||
| CN2015107629447 | 2015-11-10 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106677901A true CN106677901A (en) | 2017-05-17 |
Family
ID=58840024
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610902862.2A Pending CN106677901A (en) | 2015-11-10 | 2016-10-17 | Aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106677901A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110985207A (en) * | 2019-12-30 | 2020-04-10 | 绵阳小巨人动力设备有限公司 | Miniature double-combustion-chamber variable-circulation turbojet engine |
| CN111502830A (en) * | 2020-05-09 | 2020-08-07 | 侯宇 | Fuel-saving auxiliary thrust stealth system of aircraft engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2109974C1 (en) * | 1994-07-15 | 1998-04-27 | Арнольд Петрович Петренко | Turbojet engine |
| CN101021181A (en) * | 2006-02-13 | 2007-08-22 | 通用电气公司 | Double bypass turbofan |
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN102410110A (en) * | 2011-03-04 | 2012-04-11 | 靳北彪 | Low-entropy mixed combustion gas-liquified substance engine |
| CN102588112A (en) * | 2011-03-28 | 2012-07-18 | 摩尔动力(北京)技术股份有限公司 | Jet-flow efficient thermal power system |
| WO2015002805A1 (en) * | 2013-07-05 | 2015-01-08 | United Technologies Corporation | Gas turbine engine system for modulating flow of fan by-pass air and core engine air |
-
2016
- 2016-10-17 CN CN201610902862.2A patent/CN106677901A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2109974C1 (en) * | 1994-07-15 | 1998-04-27 | Арнольд Петрович Петренко | Turbojet engine |
| CN101021181A (en) * | 2006-02-13 | 2007-08-22 | 通用电气公司 | Double bypass turbofan |
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN102410110A (en) * | 2011-03-04 | 2012-04-11 | 靳北彪 | Low-entropy mixed combustion gas-liquified substance engine |
| CN102588112A (en) * | 2011-03-28 | 2012-07-18 | 摩尔动力(北京)技术股份有限公司 | Jet-flow efficient thermal power system |
| WO2015002805A1 (en) * | 2013-07-05 | 2015-01-08 | United Technologies Corporation | Gas turbine engine system for modulating flow of fan by-pass air and core engine air |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110985207A (en) * | 2019-12-30 | 2020-04-10 | 绵阳小巨人动力设备有限公司 | Miniature double-combustion-chamber variable-circulation turbojet engine |
| CN111502830A (en) * | 2020-05-09 | 2020-08-07 | 侯宇 | Fuel-saving auxiliary thrust stealth system of aircraft engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170517 |