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WO2025224649A1 - Pompe à jet améliorée pour système de climatisation d'aéronef - Google Patents

Pompe à jet améliorée pour système de climatisation d'aéronef

Info

Publication number
WO2025224649A1
WO2025224649A1 PCT/IB2025/054243 IB2025054243W WO2025224649A1 WO 2025224649 A1 WO2025224649 A1 WO 2025224649A1 IB 2025054243 W IB2025054243 W IB 2025054243W WO 2025224649 A1 WO2025224649 A1 WO 2025224649A1
Authority
WO
WIPO (PCT)
Prior art keywords
opening
jet pump
aircraft
duct
longitudinal axis
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
PCT/IB2025/054243
Other languages
English (en)
Inventor
Marilena NIGRO
Fabio Nannoni
Emilio Majori
Maurizio GIACOMINI
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.)
MECAER AVIATION GROUP SpA
Original Assignee
MECAER AVIATION GROUP SpA
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 MECAER AVIATION GROUP SpA filed Critical MECAER AVIATION GROUP SpA
Publication of WO2025224649A1 publication Critical patent/WO2025224649A1/fr
Pending legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
    • B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0618—Environmental Control Systems with arrangements for reducing or managing bleed air, using another air source, e.g. ram air

Definitions

  • the present invention relates to a jet pump, in particular to a jet pump for an aircraft.
  • the present invention finds a preferred, although not exclusive, application in an air conditioning system for an aircraft such as a helicopter. Said application will be referred to in the following by way of example.
  • Aircraft such as helicopters, need to heat select aircraft compartments such as, for example, the cabin.
  • jet pumps that draw hot air from the aircraft engine system and inject the same into a flow of cold air drawn from the outside environment to obtain air at a given temperature to be injected into the compartment to be heated.
  • known jet pump systems are particularly energy- intensive and poorly efficient. Furthermore, said systems are sized to provide heated air within specific temperature ranges. When used at high altitudes or in particularly cold weather conditions , known systems may not be ef fective or require an increase in the load of compressed air drawn from the engine , thus increasing consumption and reducing the autonomy and performance of the aircraft .
  • the obj ect of the present invention is to meet the above- mentioned needs in an optimi zed and inexpensive manner .
  • Figure 1 is a schematic sectional view of a j et pump for an air conditioning system according to the invention
  • Figure 1 schematically illustrates a jet pump 1 forming part of an air conditioning system (not illustrated) for an aircraft (not illustrated) .
  • the jet pump 1 can be used for an air conditioning system of a passenger and/or pilot cabin of a helicopter.
  • the jet pump 1 essentially comprises a first duct 2, or main duct, extending along a longitudinal axis A.
  • the main duct 2 defines a first opening 2a and a second opening 2b, respectively fluidically connected, for example by conduits not shown, to an outside air intake outside the aircraft and to the compartment of the vehicle to be heated.
  • the main duct 2 is coaxial with the longitudinal axis A and comprises a first end portion 2' , a second end portion 2' ’ and an intermediate portion 2’ ’ ’ longitudinally comprised between said first and second end portions 2’ , 2’ ’ .
  • the main duct 2 is made in a single piece.
  • first end portion 2’ defines the first opening 2a whereas the second end portion 2’ ’ defines the second opening 2b.
  • the main duct 2 has a variable section along the longitudinal axis A.
  • the first end portion 2’ has a constant section that is greater than the third end portion 2’ ’ ’ connected to the same.
  • the second end portion 2’ ’ has a variable section starting from a minimum value, coinciding with the section of the intermediate portion 2’ ’ ’ to a maximum value advantageously equal to the section of the first end portion 2 ’ .
  • the jet pump 1 further comprises a second duct 3, injector duct, defining a first opening 3a and a second opening 3b.
  • the inj ector duct 3 defines a first opening 3a and a second opening 3b, respectively fluidically connected, for example by pipes not shown, to a heated and high-pressure air intake coming from an engine system (not shown) , in particular from the first compression stage of a turboshaft engine , and inside the main duct 2 .
  • the f irst opening 3a is coaxial with an auxiliary axis A' , preferably parallel to the longitudinal axis A, whereas the second opening 3b faces along the longitudinal axis A, advantageously parallel to and better yet , coaxial with the same .
  • the auxiliary duct 3 comprises a first end portion 3 ' , a second end portion 3 ' ’ and an intermediate portion 3 ' ’ ’ comprised between said first and second end portions 3 ' , 3 ' ’ .
  • the auxiliary duct 3 is made in a s ingle piece , in greater detail in a material resistant to high pressures and temperatures .
  • first end portion 3 ' defines the first opening 3a whereas the second end portion 3 ' ' defines the second opening 3b .
  • the intermediate portion 3 ' ’ ’ is advantageously perpendicular to the first and second end portions 3 ’ , 3 ’ ’ that is , it extends along a vertical axis B, inclined and preferably perpendicular to the longitudinal axis A.
  • the auxiliary duct 3 has a variable section along its extension along the axes A' , B, A.
  • the intermediate portion 3 ’ ’ ’ has a substantially constant section
  • the first end portion 3 ’ has a variable section narrowing from a maximum section, at the first opening 3a, to a minimum section equal to that of the intermediate portion
  • the second end portion 3 ' has a variable section narrowing from a minimum section, at the second opening 3b, to a maximum section equal to that of the intermediate portion .
  • main and auxiliary ducts 2 , 3 have an axisymmetric shape along their respective axes , however they could have a polygonal-section shape or any shape according to process needs .
  • variable sections mentioned above are advantageously linear between the minimum and maximum sections described above ; in particular they define a Venturi type system .
  • the main ducts 2 , 3 are made of composite materials or metallic materials , preferably light ; the second of metallic material , such as steel .
  • the auxiliary duct 3 is housed within an intermediate opening 2c of the axi s B, that is , pas sing the main duct 2 transversally with respect to the longitudinal axis A longitudinally comprised between the first and second openings 2a, 2b of the main duct 2 , advantageously made in the first end portion 2 ’ .
  • the opening 2c advantageously houses a support 4 configured to house part of the intermediate portion 3 ' ’ ’ of the auxiliary duct 3 .
  • said support is cup-shaped and si zed to fit into the opening 2c .
  • the support 4 also defines an opening 4a suitable for allowing the passage of the intermediate portion 3 ' ’ ’ of the auxiliary duct 3 .
  • the latter comprises a radial flange 6 extending from the intermediate portion 3 ' ’ ’ and configured to cooperate in contact with the support 4 to prevent movement of the auxiliary duct 3 with respect to said support 4 .
  • the j et pump 1 comprises insulation means 5 interposed between the flange 6 and the support 4 and configured to prevent direct thermal transmission between the main and auxiliary ducts 2 , 3 and fluidically isolate the opening 4a of the support 4 .
  • the insulation means 5 comprise an annular element made of a polymeric material/a sealing ring .
  • the second end portion of the auxiliary duct 3 defines at least one intermediate opening 7 with an axis along the vertical axis B .
  • said axis is inclined, in particular incident and more preferably perpendicular to the longitudinal axis A.
  • two intermediate openings 7 are provided, advantageously coaxial with one another .
  • the j et pump 1 comprises a regulation system 8 configured to vary the passage section of at least one intermediate opening 7 .
  • the regulation system 8 comprises a shutter element 9 configured to assume a position between a maximum opening position in which it allows the free pas sage of fluid through the at least one intermediate opening 7 , a minimum opening position in which it prevents the passage of fluid through the at least one opening 7 or any intermediate position between the latter .
  • the regulation system 8 comprises , furthermore , actuator means (not illustrated) configured to control the shutter element 9 between the aforementioned positions .
  • the shutter element 9 is a ring fitted on the second portion 3 ' ’ so as to rotate around the same and provided with a respective opening 9a that can totally or partially overlap or block the intermediate opening ( or intermediate openings ) 7 .
  • an equal number of openings 9a can be provided on the ring 9 .
  • the heating system or the aircraft comprise sensor means conf igured to detect a physical quantity indicative of a physical state of the fluid exiting from the second opening 2b of the main duct 2 and an electronic unit comprising processing means suitable for processing the physical quantity detected by the aforementioned sensor means and providing a control signal to the actuator means to control the passage of the shutter element between the aforementioned positions .
  • the sensor means are temperature sensors , pressure sensors and/or flow meters .
  • the first opening 3a of the auxiliary duct 3 and/or the first opening 2a of the main duct 2 may also be provided to check the physical state of the incoming fluid .
  • the electronic unit is also electronically connected to input means , such as a display or a control knob/button, configured to receive an input signal indicative of a desired temperature in the portion of the aircraft to be air-conditioned and/or the temperature and/or pressure detected by the sensor means designed to check the physical state of the fluid entering the cabin from the section 2b and/or the temperatures of the fluid entering from the section 2a, and/or (where applicable ) the temperature measured in the cabin .
  • the electronic unit is also connected to the engine system or other thermal energy source of the aircraft to acquire operating data .
  • the processing means of the electronic unit are configured to process the indicative input signal received from the input means , the sensor means and, where applicable , the engine system to control , for example by a closed-loop system, the actuator means as described above .
  • the j et pump 1 receives as input , through the first opening 3a of the auxiliary duct 3 , a first inlet flow Fb at a pressure higher than the outside air pres sure and at a high temperature from an engine system of the aircraft . Said first flow exits from the second opening 3b providing a first internal flow Fc . Said inj ection of fluid into the main duct 2 draws , from the first opening 2a of the latter, a second inlet flow Fa from the outside environment which therefore tends to mix with the first internal flow Fc to provide an outlet flow Fe towards the compartment to be air conditioned .
  • I f one or more intermediate openings 7 are provided in the second end portion 3 ' ’ of the auxiliary duct 3 , part of the first inlet flow Fb exits from the same , perpendicular to the first portion, as a second internal flow Fd inside the main duct 2 upstream of the second opening 3b of the auxiliary duct 3 .
  • the mixing of the first and second inlet flows Fb, Fa is signi ficantly increased without increasing the drag ef fect on the flow entering from the section 2a and therefore without increasing the flow rate of cold air aspirated, thus providing a mixed outlet flow Fe with practically the same flow rate but at a signi ficantly higher temperature .
  • I f one or more intermediate openings 7 provided with a regulation system 8 are provided, the operation is similar to that described above , in particular it is possible to vary the value of the second internal f low Fd between a zero value and a maximum value corresponding to a complete blockage or opening of one or more intermediate openings 7 .
  • the electronic unit comprises processing means to process the data acquired by the engine system, the input means , the sensor means to control the regulation system 8 .
  • the processing clearly uses thermodynamic laws that link the need for air conditioning o f the vehicle portion with the physical characteristics of the fluids entering the j et pump and therefore not disclosed for the sake of brevity, being able to vary depending on the speci fic use and aircraft needs .
  • the invention is therefore also related to a method for controlling a j et pump 1 in an aircraft as described above , comprising the steps of : i ) acquiring data from the sensor means , the input means , and the engine system; ii ) processing a control signal based on the data acquired in point ii ) to control the regulation system to define a percentage of blockage of the at least one intermediate opening ( 7 ) .
  • the method described above can be performed continuously or at given intervals , i f air conditioning of the aircraft compartment is required .
  • the aforementioned mixing moreover, allows to signi ficantly increase the temperature of the fluid at the outlet , in particular by 50- 100% compared to the systems of the prior art .
  • the higher outlet temperature allows to have to draw less fluid or fluid at a lower temperature from the engine system, allowing a substantial energy saving . Furthermore, this makes the j et pump ef fective in conditions where , in the absence of the system described here , it could not guarantee the flow rates of hot air required by the aircraft heating system .
  • the regulation system it is also possible to regulate the functionality of the aforementioned openings between a minimum and a maximum value , achieving further energy savings depending on the vehicle needs and external atmospheric conditions .
  • the suggested shutter system is particularly compact and has minimal influence on the internal fluid dynamics of the duct 2 .
  • the supplied shutter system is particularly inexpensive and easy to produce .
  • the shape of the ducts can vary, as well as their mutual assembly.
  • the second end portion 3' can have convergent- divergent shapes (so-called De Lavall nozzle) .
  • De Lavall nozzle convergent- divergent shapes
  • different shapes and numbers of intermediate openings could be foreseen.
  • the shutter system as mentioned, can be omitted or can be made differently than described.

Landscapes

  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Pompe à jet (11) pour système de conditionnement d'air d'un aéronef, comprenant un premier conduit (2) s'étendant selon un axe longitudinal (A) définissant une première et une seconde ouvertures (2a, 2b) respectivement raccordables fluidiquement à une entrée d'air extérieur et à une partie de l'aéronef à conditionner, un second conduit (3) définissant une première et une seconde ouvertures (3a, 3b), la première ouverture (3a) étant raccordable fluidiquement à un système moteur de l'aéronef et la seconde ouverture (3b) étant disposée à l'intérieur du premier conduit (2) entre la première et la seconde ouvertures (2a, 2b), le second conduit (3) définissant au moins une ouverture intermédiaire (7) réalisée entre les première et seconde ouvertures (3a, 3b), l'ouverture intermédiaire (7) ayant un axe (B) incliné par rapport à l'axe longitudinal (A).
PCT/IB2025/054243 2024-04-24 2025-04-23 Pompe à jet améliorée pour système de climatisation d'aéronef Pending WO2025224649A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT102024000009505 2024-04-24
IT202400009505 2024-04-24

Publications (1)

Publication Number Publication Date
WO2025224649A1 true WO2025224649A1 (fr) 2025-10-30

Family

ID=91966340

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2025/054243 Pending WO2025224649A1 (fr) 2024-04-24 2025-04-23 Pompe à jet améliorée pour système de climatisation d'aéronef

Country Status (1)

Country Link
WO (1) WO2025224649A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060168958A1 (en) * 2005-01-02 2006-08-03 Jan Vetrovec Supercharged internal combustion engine
US8303384B2 (en) 2006-04-11 2012-11-06 Airbus Deutschland Gmbh Device for mixing fresh air and heating air and use of the device in a ventilation system of an aircraft
US20160288913A1 (en) 2013-07-10 2016-10-06 Liebherr-Aerospace Toulouse Sas Gas mixing pump, particularly for a heating system
US20180057173A1 (en) * 2016-08-23 2018-03-01 Ge Aviation Systems, Llc Hybrid method and aircraft for pre-cooling an environmental control system using a power generator four wheel turbo-machine
US10556693B2 (en) * 2017-02-23 2020-02-11 Liebherr-Aerospace Toulouse Sas Method for ventilating a ram air channel and environmental control device and vehicle implementing this method
US20230392615A1 (en) * 2022-06-07 2023-12-07 Honeywell International Inc. Jet pump system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060168958A1 (en) * 2005-01-02 2006-08-03 Jan Vetrovec Supercharged internal combustion engine
US8303384B2 (en) 2006-04-11 2012-11-06 Airbus Deutschland Gmbh Device for mixing fresh air and heating air and use of the device in a ventilation system of an aircraft
US20160288913A1 (en) 2013-07-10 2016-10-06 Liebherr-Aerospace Toulouse Sas Gas mixing pump, particularly for a heating system
US20180057173A1 (en) * 2016-08-23 2018-03-01 Ge Aviation Systems, Llc Hybrid method and aircraft for pre-cooling an environmental control system using a power generator four wheel turbo-machine
US10556693B2 (en) * 2017-02-23 2020-02-11 Liebherr-Aerospace Toulouse Sas Method for ventilating a ram air channel and environmental control device and vehicle implementing this method
US20230392615A1 (en) * 2022-06-07 2023-12-07 Honeywell International Inc. Jet pump system

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