CN108005792A - A kind of air turbine starter turbine stage arrangement - Google Patents

A kind of air turbine starter turbine stage arrangement Download PDF

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Publication number
CN108005792A
CN108005792A CN201711083401.8A CN201711083401A CN108005792A CN 108005792 A CN108005792 A CN 108005792A CN 201711083401 A CN201711083401 A CN 201711083401A CN 108005792 A CN108005792 A CN 108005792A
Authority
CN
China
Prior art keywords
turbine
guider
stage arrangement
starter
housing
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
CN201711083401.8A
Other languages
Chinese (zh)
Inventor
高瞻
刘冕
熊欣
王赫
苏中亮
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.)
Jincheng Nanjing Electromechanical Hydraulic Pressure Engineering Research Center Aviation Industry Corp of China
AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
Original Assignee
AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
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 AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems filed Critical AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
Priority to CN201711083401.8A priority Critical patent/CN108005792A/en
Publication of CN108005792A publication Critical patent/CN108005792A/en
Pending legal-status Critical Current

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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F02C7/277—Mechanical drives the starter being a separate turbine
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade

Landscapes

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

Abstract

The present invention relates to a kind of air turbine starter turbine stage arrangement.The device is mainly used for the interior energy in the high temperature and pressure incoming for extracting specific accessory power system offer, and it is converted into 100kW power grade shaft power.The present apparatus is mainly made of guider, turbine and housing.Wherein, guider is installed in housing by screw, and guider downstream is turbine, and turbine stretches into enclosure interior, and keeps gap with guider and housing.When air turbine starter works, high temperature and pressure incoming is limited in housing, impacts guider, band rotating turbine, produces shaft power.The present apparatus is simple in structure, and reliability is high；The specific incoming that accessory power system provides is matched, the shaft power of 100kW power grades is exported, there is larger actual application value.

Description

A kind of air turbine starter turbine stage arrangement
Technical field
The invention belongs to aviation accessory power system, is related to a kind of air turbine starter turbine stage arrangement.
Background technology
Air turbine starter is the part in aviation accessory power system.Its operation principle is by being aided in by aviation The turbine stage arrangement for the high pressure draught impinging air turbo-starter that dynamical system provides, drives turbine rotation, is risen to engine Dynamic drive system chain output shaft power, drives engine to start.After band forwarding motivation reaches certain rotating speed, air turbine starts Machine is stopped, and departs from engine starting system driving-chain.
During being somebody's turn to do, it need to complete to change impulse turbine after airintake direction by stator blade by high pressure draught, drive Turbine rotation, shaft power is exported to engine starting system driving-chain.
In the prior art, no turbine stage arrangement can match specific aviation accessory power system needed for this model and provide High pressure draught, export the shaft power of 100kW power grades, therefore the design of serious limitation air turbine starter.
The content of the invention
The purpose of the present invention：A kind of air turbine starter turbine stage arrangement compact-sized, reliability is high is provided.
Technical scheme：A kind of air turbine starter turbine stage arrangement, including：Guider, turbine and housing Composition.Wherein, guider is installed in housing, and guider downstream is turbine, and turbine stretches into enclosure interior, and with guider and shell Body keeps gap.
Beneficial effects of the present invention：The present invention provides a kind of air turbine starter turbine stage arrangement.It is dynamic that auxiliary can be matched The specific incoming that Force system provides, exports the shaft power of 100kW power grades.The present invention is pure mechanic structure, it is not necessary to annex Control element, automatically completes the accelerator of air turbine starter output speed.Each design of part is simple, to material and adds Work technique is without particular/special requirement, production cost bottom.
Brief description of the drawings：
Fig. 1 is a kind of structure diagram of air turbine starter turbine stage arrangement of the present invention；
Wherein, 1- housings, 2- screws, 3- guiders, 4- turbines.
Fig. 2 show guider, and Fig. 3 show stator blade, and Fig. 4 show turbine, Fig. 5 turbo blades.
Embodiment
Below by embodiment, the present invention is described in further detail.
Please refer to Fig. 1, Fig. 1 is the structure diagram of air turbine starter turbine stage arrangement of the present invention.It is of the invention empty Air turbine starter turbine stage arrangement includes the guider 3 being installed on by screw 2 in housing 1, and 3 downstream of guider is turbine 4, Turbine 4 is stretched into inside housing 1, and turbine 4 stretches into the coincidence of 1 central axis of housing, and circumferencial direction keeps gap H.
There are 22 blades on the guider, be uniformly distributed along the circumference, internal diameter is (Φ 145 ± 0.5) mm, and outside diameter is Φ (175 ~175.03) mm.After blade along the circumferential direction profile expansion, vane foil is by leading edge, trailing edge, pressure face and suction surface group Into.Leading edge is the circular arc of one section of a diameter of Φ 1.5mm.Trailing edge is the circular arc of one section of a diameter of Φ 0.33mm.Establish as shown in Figure 3 Coordinate system.
Have on the turbine along 45 uniformly distributed blades of turbine disk outer circumference, turbine rod and be located at turbine disk side.Leaf Piece internal diameter on turbine diameter direction is Φ (142.9~144.5) mm, and outside diameter is Φ (177.45~177.5) mm, circumferentially side After being unfolded to profile, vane foil is made of leading edge, trailing edge, pressure face and suction surface.Leading edge is one section of a diameter of Φ The circular arc of 0.583mm.Trailing edge is the circular arc of one section of a diameter of Φ 0.280mm.Establish coordinate system as shown in Figure 5.Have on turbine rod Two a diameter of Φ 17mm bearing fits faces, two bearings mating surface is at a distance of (23 ± 3) mm.
It is (0.5~0.8) mm that the turbine 4 keeps the scope of gap H with housing 1 in radial direction.
When air turbine starter turbine stage arrangement works in the present invention, flow 1.2kg/s, pressure is 0.28MPa (tables Pressure) high pressure draught flow through guider along housing, producing certain air-flow along stator blade blade profile deflects, after flowing out guider Impulse turbine, after driving turbine rotation to reach 3500r/min, rear end driving-chain exports the shaft power of 100kW grades.

Claims (7)

  1. A kind of 1. air turbine starter turbine stage arrangement, it is characterised in that：Guider (3) is installed on housing by screw (2) (1) in, guider (3) downstream is turbine (4), and it is internal that turbine (4) stretches into housing (1)；Turbine (4) stretches into housing (1) central shaft Line overlaps, and circumferencial direction keeps gap.
  2. 2. air turbine starter turbine stage arrangement according to claim 1, it is characterised in that：Leading on the guider It is 22 to the device number of blade, is uniformly distributed along the circumference, internal diameter is (Φ 145 ± 0.5) mm, and outside diameter is Φ (175~175.03) mm.
  3. 3. air turbine starter turbine stage arrangement according to claim 2, it is characterised in that：The stator blade edge After the expansion of circumferencial direction profile, vane foil is made of leading edge, trailing edge, pressure face and suction surface；The leading edge is straight for one section Footpath is the circular arc of Φ 1.5mm；Trailing edge is the circular arc of one section of a diameter of Φ 0.33mm.
  4. 4. air turbine starter turbine stage arrangement according to claim 1, it is characterised in that：There is edge on the turbine 45 uniformly distributed blades of turbine disk outer circumference, internal diameter are 142.9~144.5mm of Φ, and outside diameter is 177.45~177.5mm of Φ, Turbine rod (7) is located at turbine disk side.
  5. 5. air turbine starter turbine stage arrangement according to claim 4, it is characterised in that：Blade on the turbine After along the circumferential direction profile expansion, vane foil is made of leading edge, trailing edge, pressure face and suction surface, and leading edge is one section of diameter For the circular arc of Φ 0.583mm, trailing edge is the circular arc of one section of a diameter of Φ 0.280mm.
  6. 6. air turbine starter turbine stage arrangement according to claim 4, it is characterised in that：On the turbine rod (7) There are two a diameter of Φ 17mm bearing fits faces, two bearings mating surface is at a distance of 23 ± 3mm.
  7. 7. air turbine starter turbine stage arrangement according to claim 1, it is characterised in that：The turbine (4) and shell It is 0.5~0.8mm that body (1) keeps the scope of gap H in radial direction.
CN201711083401.8A 2017-11-06 2017-11-06 A kind of air turbine starter turbine stage arrangement Pending CN108005792A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201711083401.8A CN108005792A (en) 2017-11-06 2017-11-06 A kind of air turbine starter turbine stage arrangement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201711083401.8A CN108005792A (en) 2017-11-06 2017-11-06 A kind of air turbine starter turbine stage arrangement

Publications (1)

Publication Number Publication Date
CN108005792A true CN108005792A (en) 2018-05-08

Family

ID=62051350

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201711083401.8A Pending CN108005792A (en) 2017-11-06 2017-11-06 A kind of air turbine starter turbine stage arrangement

Country Status (1)

Country Link
CN (1) CN108005792A (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2825531A (en) * 1954-07-01 1958-03-04 Gen Electric Speed limiting arrangement
US20050058542A1 (en) * 2003-09-12 2005-03-17 Kruegel Roy F. Air turbine starter with unitary inlet and stator
CN202645736U (en) * 2011-12-29 2013-01-02 中国航空工业集团公司金城南京机电液压工程研究中心 APU core machine
CN103670533A (en) * 2012-08-29 2014-03-26 哈米尔顿森德斯特兰德公司 Air turbine starter turbine nozzle wing section
CN205446898U (en) * 2015-12-24 2016-08-10 长春航空液压控制有限公司 Integrated form control air vent valve
EP3073062A1 (en) * 2015-03-24 2016-09-28 Ingersoll-Rand Company Fluid powered starter with a variable turbine stator
CN205743995U (en) * 2016-06-23 2016-11-30 中国航空动力机械研究所 Overall guider and aero-engine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2825531A (en) * 1954-07-01 1958-03-04 Gen Electric Speed limiting arrangement
US20050058542A1 (en) * 2003-09-12 2005-03-17 Kruegel Roy F. Air turbine starter with unitary inlet and stator
CN202645736U (en) * 2011-12-29 2013-01-02 中国航空工业集团公司金城南京机电液压工程研究中心 APU core machine
CN103670533A (en) * 2012-08-29 2014-03-26 哈米尔顿森德斯特兰德公司 Air turbine starter turbine nozzle wing section
EP3073062A1 (en) * 2015-03-24 2016-09-28 Ingersoll-Rand Company Fluid powered starter with a variable turbine stator
CN205446898U (en) * 2015-12-24 2016-08-10 长春航空液压控制有限公司 Integrated form control air vent valve
CN205743995U (en) * 2016-06-23 2016-11-30 中国航空动力机械研究所 Overall guider and aero-engine

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Application publication date: 20180508