CN106194497A - Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure - Google Patents

Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure Download PDF

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Publication number
CN106194497A
CN106194497A CN201610452264.XA CN201610452264A CN106194497A CN 106194497 A CN106194497 A CN 106194497A CN 201610452264 A CN201610452264 A CN 201610452264A CN 106194497 A CN106194497 A CN 106194497A
Authority
CN
China
Prior art keywords
gas turbine
jet engine
aero
casing
combustion chamber
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
Application number
CN201610452264.XA
Other languages
Chinese (zh)
Inventor
杨京生
张永立
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to CN201610452264.XA priority Critical patent/CN106194497A/en
Publication of CN106194497A publication Critical patent/CN106194497A/en
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure, belong to aero-jet engine professional field.Its pneumatic principle is identical with general aviation electromotor, but working method is contrary.Traditional aero-jet engine is that casing is fixed on fuselage, under the effect of combustion gas, drives fan and compressor to be operated by the gas turbine on main shaft.The present invention is that the rotor of compressor is made of one with casing, and again by tubular gas turbine during assembling, casing and the fan of band rotor are linked, and composition one is fixing.Axis, in addition to installing the stator of compressor, is mainly used in the configuration of oil circuit and Circuits System.Operation principle is: under the effect of combustion gas, promotes gas turbine, linkage compressor and fan to be operated, produces motive force.

Description

Fixing shaft type, tubular gas turbine, the turbofan aerojet of single combustion chamber structure Electromotor
Technical field: aero-jet engine.
Background technology: up to now, all aero-jet engines both domestic and external, for ease of fixed installation, all use fixing Casing, under combustion gas effect, the mode being operated by the compressor on gas turbine linkage main shaft produces thrust.This aviation is sprayed Gas electromotor, identical with general aviation jet engine on pneumatic principle, but in design by anti-phase thinking, be allowed to and pass The aero-jet engine working method of system is contrary, and namely main shaft maintains static, by fan, gas turbine, the machine of compressor Casket joins together, and under the effect of combustion gas, the rotation generation thrust by casing is operated.
Summary of the invention:
1., with modern Aviation jet engine: axle moves, shell is motionless the most contrary, is that axle is motionless, the working method that shell is dynamic.
The most coolable high aspect ratio, the tubular combustion gas turbine of hollow blade.
3. single combustion chamber structure.
Accompanying drawing illustrates:
Fig. 1 is tubular gas turbine rearview；
Fig. 2 is fan and Profile For Compressor Stator three-dimensional structure diagram；
Fig. 3 is compressor sectional view；
Fig. 4 is to regard outside the turbofan core engine fixing shaft type, tubular gas turbine, single combustion chamber structure Figure.

Claims (1)

1. although the present invention is identical with the pneumatic principle of modern Aviation jet engine, but working method is just contrary, main region Do not exist:
The working method of the most domestic and international all of aero-jet engine, entirely casing is fixed, and carries out work by shaft power Make.This aero-jet engine working method is just contrary, but uses fixing axle, is installed on casing by compressor rotor, Casing, linkage fan is driven to be operated by drum-type gas turbine.
2. drum-type gas turbine, is that this boat sends out the distinguishing mark being different from current aero-jet engine disc type gas turbine.
The drum-type gas turbine that this boat is sent out have employed the hollow of high aspect ratio can cooling blade.
3. the aero-jet engine in modern times is commonly used ring-like or tubular combustor, the unique single combustion chamber knot of this boat hair Structure.
Require: carry out patent guarantor to using fixing shaft type, drum-type gas turbine, the aero-jet engine of single combustion chamber structure Protect.
CN201610452264.XA 2016-06-21 2016-06-21 Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure Pending CN106194497A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201610452264.XA CN106194497A (en) 2016-06-21 2016-06-21 Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610452264.XA CN106194497A (en) 2016-06-21 2016-06-21 Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure

Publications (1)

Publication Number Publication Date
CN106194497A true CN106194497A (en) 2016-12-07

Family

ID=57460691

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201610452264.XA Pending CN106194497A (en) 2016-06-21 2016-06-21 Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure

Country Status (1)

Country Link
CN (1) CN106194497A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108412636A (en) * 2018-03-07 2018-08-17 杨京生 Fanjet core engine for aviation power field

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1115004A (en) * 1995-04-20 1996-01-17 郭颖 Reaction type jet engine
CN2305492Y (en) * 1996-06-17 1999-01-27 尹群 Counter rotational gas turbine engine
US20080148707A1 (en) * 2006-12-21 2008-06-26 Jan Christopher Schilling Turbofan engine assembly and method of assembling same
CN102305152A (en) * 2011-05-20 2012-01-04 中国科学院工程热物理研究所 Hybrid exhaust aircraft engine
CN103775245A (en) * 2012-10-26 2014-05-07 徐建宁 Rotating type combustion chamber jet engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1115004A (en) * 1995-04-20 1996-01-17 郭颖 Reaction type jet engine
CN2305492Y (en) * 1996-06-17 1999-01-27 尹群 Counter rotational gas turbine engine
US20080148707A1 (en) * 2006-12-21 2008-06-26 Jan Christopher Schilling Turbofan engine assembly and method of assembling same
CN102305152A (en) * 2011-05-20 2012-01-04 中国科学院工程热物理研究所 Hybrid exhaust aircraft engine
CN103775245A (en) * 2012-10-26 2014-05-07 徐建宁 Rotating type combustion chamber jet engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108412636A (en) * 2018-03-07 2018-08-17 杨京生 Fanjet core engine for aviation power field

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Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20161207

WD01 Invention patent application deemed withdrawn after publication