FR3143064B1 - Turbomachine pour aeronef - Google Patents

Turbomachine pour aeronef Download PDF

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Publication number
FR3143064B1
FR3143064B1 FR2213215A FR2213215A FR3143064B1 FR 3143064 B1 FR3143064 B1 FR 3143064B1 FR 2213215 A FR2213215 A FR 2213215A FR 2213215 A FR2213215 A FR 2213215A FR 3143064 B1 FR3143064 B1 FR 3143064B1
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France
Prior art keywords
pressure
low
turbomachine
compressor
aircraft
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
FR2213215A
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English (en)
Other versions
FR3143064A1 (fr
Inventor
Jérémy Edmond Fert
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
Original Assignee
Safran Aircraft Engines SAS
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.)
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2213215A priority Critical patent/FR3143064B1/fr
Publication of FR3143064A1 publication Critical patent/FR3143064A1/fr
Application granted granted Critical
Publication of FR3143064B1 publication Critical patent/FR3143064B1/fr
Active 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
    • 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
    • F02C3/145—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 the combustion chamber being in the reverse flow-type
    • 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
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure

Landscapes

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

Abstract

L’invention concerne une turbomachine (4) comprenant : - un corps basse pression (6) comprenant un compresseur basse pression (8) et une turbine basse pression (9), - un corps haute pression (7) comprenant un compresseur haute pression (12) et une turbine haute pression (11), et - une chambre de combustion (23), - le corps haute pression (7) est agencé à l’arrière du corps basse pression (6), et le compresseur haute pression (12) est situé à l’arrière de la turbine haute pression (11), - la chambre de combustion (23) est située à l’arrière de la turbine haute pression (11), voire du compresseur haute pression (12), et en ce qu’elle comprend en outre un système d’alimentation (24) de la chambre de combustion (23) en gaz combustible, ce système d’alimentation (24) étant situé à l’arrière de la turbine haute pression (11), voire du compresseur haute pression (12). Figure d’abrégé : figure 2
FR2213215A 2022-12-13 2022-12-13 Turbomachine pour aeronef Active FR3143064B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2213215A FR3143064B1 (fr) 2022-12-13 2022-12-13 Turbomachine pour aeronef

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2213215A FR3143064B1 (fr) 2022-12-13 2022-12-13 Turbomachine pour aeronef
FR2213215 2022-12-13

Publications (2)

Publication Number Publication Date
FR3143064A1 FR3143064A1 (fr) 2024-06-14
FR3143064B1 true FR3143064B1 (fr) 2024-11-29

Family

ID=85222436

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2213215A Active FR3143064B1 (fr) 2022-12-13 2022-12-13 Turbomachine pour aeronef

Country Status (1)

Country Link
FR (1) FR3143064B1 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1370887A (en) * 1970-09-26 1974-10-16 Secr Defence Aircraft and gas turbine engines therefor
US9140212B2 (en) * 2012-06-25 2015-09-22 United Technologies Corporation Gas turbine engine with reverse-flow core having a bypass flow splitter
US10794273B2 (en) * 2015-07-01 2020-10-06 Raytheon Technologies Corporation Advanced distributed engine architecture-design alternative
US10378438B2 (en) * 2016-04-20 2019-08-13 Rolls-Royce North American Technologies, Inc. Reverse flow gas turbine engine with radially outward turbine
US20210262416A1 (en) * 2020-02-20 2021-08-26 General Electric Company Turbofan engine with core exhaust and bypass flow mixing

Also Published As

Publication number Publication date
FR3143064A1 (fr) 2024-06-14

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