FR3094030B1 - Ensemble propulsif d’aeronef - Google Patents

Ensemble propulsif d’aeronef Download PDF

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Publication number
FR3094030B1
FR3094030B1 FR1902987A FR1902987A FR3094030B1 FR 3094030 B1 FR3094030 B1 FR 3094030B1 FR 1902987 A FR1902987 A FR 1902987A FR 1902987 A FR1902987 A FR 1902987A FR 3094030 B1 FR3094030 B1 FR 3094030B1
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France
Prior art keywords
casing
scoop
stream
aircraft power
power package
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Active
Application number
FR1902987A
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English (en)
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FR3094030A1 (fr
Inventor
Bastien Pierre Verdier
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.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1902987A priority Critical patent/FR3094030B1/fr
Publication of FR3094030A1 publication Critical patent/FR3094030A1/fr
Application granted granted Critical
Publication of FR3094030B1 publication Critical patent/FR3094030B1/fr
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Classifications

    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • 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
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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)
  • Packaging Of Machine Parts And Wound Products (AREA)

Abstract

La présente invention concerne un ensemble propulsif (10) d’aéronef, d’axe longitudinal (A), comportant un moteur comprenant un premier carter (17) de révolution et une nacelle (14) comprenant un second carter (16) de révolution délimitant avec le premier carter (17) une veine annulaire d’écoulement (22) d’un flux d’air, ledit ensemble (10) comprenant en outre une écope (30) de prélèvement d’air dans ladite veine (22) traversant l’un ou l’autre des premier ou second carter, l’écope (30) comprenant une première partie de prélèvement d’air (30a) dans la veine(22) et une seconde partie (30b) opposée à ladite première partie (30a) et positionnée en dehors de la veine (22), l’ensemble propulsif (10) étant caractérisé en ce que la première partie (30a) de l’écope (30) est montée à rotation par rapport à la seconde partie (30b). Figure pour l’abrégé : Figure 10
FR1902987A 2019-03-22 2019-03-22 Ensemble propulsif d’aeronef Active FR3094030B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1902987A FR3094030B1 (fr) 2019-03-22 2019-03-22 Ensemble propulsif d’aeronef

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1902987 2019-03-22
FR1902987A FR3094030B1 (fr) 2019-03-22 2019-03-22 Ensemble propulsif d’aeronef

Publications (2)

Publication Number Publication Date
FR3094030A1 FR3094030A1 (fr) 2020-09-25
FR3094030B1 true FR3094030B1 (fr) 2021-06-04

Family

ID=67185438

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1902987A Active FR3094030B1 (fr) 2019-03-22 2019-03-22 Ensemble propulsif d’aeronef

Country Status (1)

Country Link
FR (1) FR3094030B1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8096498B2 (en) * 2007-12-12 2012-01-17 Hamilton Sundstrand Corporation Rotating auxiliary power unit air inlet door
GB201212072D0 (en) * 2012-07-06 2012-08-22 Rolls Royce Plc Fluid intake and system for rotary machines
US10196936B2 (en) * 2013-03-15 2019-02-05 United Technologies Corporation Air oil cooler airflow augmentation system
DE102014217830A1 (de) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Luftleitvorrichtung und Turbomaschine mit Luftleitvorrichtung

Also Published As

Publication number Publication date
FR3094030A1 (fr) 2020-09-25

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