FR3074849B1 - Turbomachine d'aeronef a au moins deux corps comprenant des moyens de derivation de gaz comprimes - Google Patents

Turbomachine d'aeronef a au moins deux corps comprenant des moyens de derivation de gaz comprimes Download PDF

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Publication number
FR3074849B1
FR3074849B1 FR1762086A FR1762086A FR3074849B1 FR 3074849 B1 FR3074849 B1 FR 3074849B1 FR 1762086 A FR1762086 A FR 1762086A FR 1762086 A FR1762086 A FR 1762086A FR 3074849 B1 FR3074849 B1 FR 3074849B1
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FR
France
Prior art keywords
low pressure
compressed gas
bypass means
gas bypass
including compressed
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.)
Active
Application number
FR1762086A
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English (en)
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FR3074849A1 (fr
Inventor
Nicolas Jerome Jean Tantot
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 FR1762086A priority Critical patent/FR3074849B1/fr
Publication of FR3074849A1 publication Critical patent/FR3074849A1/fr
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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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Control Of Turbines (AREA)

Abstract

Turbomachine (10) d'aéronef à au moins deux corps, comprenant au moins un corps basse pression (20) comprenant une soufflante (40), un compresseur basse pression (22) et une turbine basse pression (24), et au moins un corps haute pression (30) comprenant un compresseur haute pression (32) et une turbine haute pression (34), caractérisée en ce que la turbomachine (10) comprend en outre des moyens de dérivation (50) de gaz comprimés, qui comportent au moins une conduite (52) de dérivation agencée entre le compresseur basse pression (22) et la turbine basse pression (24), pour alimenter directement la turbine basse pression (24) avec des gaz comprimés sortant du compresseur basse pression (22), et au moins une vanne (60) configurée pour laisser passer dans ladite au moins une conduite (52) un débit de gaz comprimés qui est fonction d'un paramètre de régulation de la commande de ladite au moins une vanne (60).
FR1762086A 2017-12-13 2017-12-13 Turbomachine d'aeronef a au moins deux corps comprenant des moyens de derivation de gaz comprimes Active FR3074849B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1762086A FR3074849B1 (fr) 2017-12-13 2017-12-13 Turbomachine d'aeronef a au moins deux corps comprenant des moyens de derivation de gaz comprimes

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1762086 2017-12-13
FR1762086A FR3074849B1 (fr) 2017-12-13 2017-12-13 Turbomachine d'aeronef a au moins deux corps comprenant des moyens de derivation de gaz comprimes

Publications (2)

Publication Number Publication Date
FR3074849A1 FR3074849A1 (fr) 2019-06-14
FR3074849B1 true FR3074849B1 (fr) 2020-11-06

Family

ID=61224112

Family Applications (1)

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FR1762086A Active FR3074849B1 (fr) 2017-12-13 2017-12-13 Turbomachine d'aeronef a au moins deux corps comprenant des moyens de derivation de gaz comprimes

Country Status (1)

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FR (1) FR3074849B1 (fr)

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120167587A1 (en) * 2010-12-30 2012-07-05 Robert Earl Clark Gas turbine engine with bleed air system
US10578028B2 (en) * 2015-08-18 2020-03-03 General Electric Company Compressor bleed auxiliary turbine

Also Published As

Publication number Publication date
FR3074849A1 (fr) 2019-06-14

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