DE899588C - Gas turbine, especially for pressurized aircraft cabins - Google Patents

Gas turbine, especially for pressurized aircraft cabins

Info

Publication number
DE899588C
DE899588C DES21488A DES0021488A DE899588C DE 899588 C DE899588 C DE 899588C DE S21488 A DES21488 A DE S21488A DE S0021488 A DES0021488 A DE S0021488A DE 899588 C DE899588 C DE 899588C
Authority
DE
Germany
Prior art keywords
gas turbine
compressor
turbine
combustion chamber
aircraft cabins
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.)
Expired
Application number
DES21488A
Other languages
German (de)
Inventor
Joseph Szydlowski
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Application granted granted Critical
Publication of DE899588C publication Critical patent/DE899588C/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft eine Gasturbine,, deren Verdichter so bemessen ist, daß er diese Turbine speisen und außerdem Nutzdruckluft, insbesondere für Überdruckkabinen von Flugzeugen, liefern kann. Erfindungsgemäß wird die Nutzdruckluft vom Verdichter in eine die Verbrennungskammer der Gasturbine umgebende Leitung gefördert. Der Verdichter, die Verbrennungskammer, die Turbine und die Leitung, welche die Form einer SpiraleThe invention relates to a gas turbine, whose Compressor is dimensioned so that it feeds this turbine and also useful compressed air, in particular for pressurized cabins of aircraft. According to the invention, the useful compressed air conveyed by the compressor into a line surrounding the combustion chamber of the gas turbine. Of the Compressor, the combustion chamber, the turbine and the conduit, which is in the shape of a spiral

ίο hat, sind gleichachsig angeordnet. Diese Anordnung gewährleistet eine Verminderung des Gewichts· der Drucklufterzeugungsaggregate, was insbesondere für Flugzeuge einen wichtigen Vorteil darstellt.ίο are arranged coaxially. This arrangement ensures a reduction in the weight · of the compressed air generating units, which in particular represents an important advantage for aircraft.

Die Erfindung ist in der nachstehenden Be-Schreibung erläutert, welche auf die einzige, nur beispielshalber angegebene Abbildung Bezug nimmt.The invention is in the description below explains which reference is made to the only figure given by way of example only takes.

Ein Fliehkraftverdichter 1 saugt Atmosphärenluft durch einen zwischen dem Gehäuse 3 und der Mittelhaube 4 angeordneten Diffusor 2 an. Die von dem Fliehkraftverdidhter 1 angesaugte Luft wird einerseits in eine Leitung 5 und andererseits in die Verbrennungskammer 6 gefördert.A centrifugal compressor 1 sucks atmospheric air through between the housing 3 and the Middle hood 4 arranged diffuser 2 on. The air sucked in by the centrifugal compressor 1 is conveyed on the one hand in a line 5 and on the other hand in the combustion chamber 6.

Beim Austritt aus der Verbrennungskammer durchströmen die Gase eine ein- oder mehrstufige Turbine 7 und werden anschließend durch eine zwischen der Mittelhaube 9 und dem Abfuhrgehäuse 10 ,gebildete Leitung 8 abgeführt.When exiting the combustion chamber, the gases flow through a single or multi-stage Turbine 7 and are then carried by a between the central hood 9 and the discharge housing 10, formed line 8 discharged.

Die NutzdrucMuft wird in der Leitung 5 aufgefangen, wo sie durch Anzapfungen der bei 11 dargestellten Art entnommen wird. Die gesamte von der Turbine gelieferte Leistung wird dem Verdichter zugeführt. Der Verdichter wie auch die Verbrennungskammer können eine beliebige Bauart aufweisen.The useful pressure is collected in line 5, where it is taken by taps of the type shown at 11. The whole Power delivered by the turbine is fed to the compressor. The compressor as well as the Combustion chambers can be of any type.

Claims (2)

PATENTANSPRÜCHE:PATENT CLAIMS: i. Gasturbine, deren Verdichter so bemessen ist, daß er diese Turbine speisen und außerdem Nutzdruckluft, insbesondere für Überdruckkabinen von Flugzeugen, liefern kann, dadurch gekennzeichnet, daß die Nutzdruckluft vom Verdichter in eine die Verbrennungskammer der Gasturbine umgebende Leitung (5, na) gefördert wird.i. Gas turbine whose compressor is so sized is that it feeds this turbine and also supplies useful compressed air, especially for pressurized cabins of aircraft can, characterized in that the useful compressed air from the compressor into a combustion chamber the gas turbine surrounding line (5, na) is promoted. 2. Gasturbine nach Anspruch 1, dadurch gekennzeichnet, daß der Verdichter (1), die Verbrennungskammer (6), .die Turbine (7) und die Leitung (11), welche die Form einer Spirale hat, gleichachsig angeordnet sind.2. Gas turbine according to claim 1, characterized characterized in that the compressor (1), the combustion chamber (6), .the turbine (7) and the line (11), which has the shape of a spiral, are arranged coaxially. Hierzu ι Blatt ZeichnungenFor this purpose ι sheet of drawings
DES21488A 1950-02-22 1951-01-09 Gas turbine, especially for pressurized aircraft cabins Expired DE899588C (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR899588X 1950-02-22

Publications (1)

Publication Number Publication Date
DE899588C true DE899588C (en) 1953-12-14

Family

ID=9392350

Family Applications (1)

Application Number Title Priority Date Filing Date
DES21488A Expired DE899588C (en) 1950-02-22 1951-01-09 Gas turbine, especially for pressurized aircraft cabins

Country Status (3)

Country Link
DE (1) DE899588C (en)
FR (1) FR1013172A (en)
GB (1) GB697119A (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2673845A1 (en) * 1991-03-13 1992-09-18 Drecq Daniel Autonomous device for generating compressed air, and recompression casing incorporating it
DE102010002114A1 (en) * 2010-02-18 2011-08-18 Rolls-Royce Deutschland Ltd & Co KG, 15827 Gas turbine with a bleed air device for the compressor

Also Published As

Publication number Publication date
FR1013172A (en) 1952-07-23
GB697119A (en) 1953-09-16

Similar Documents

Publication Publication Date Title
DE102009047083A1 (en) Compressed air operated vacuum generator or vacuum gripper
DE1428220C3 (en) By-pass gas turbine jet engine in two-shaft design
EP0769655A3 (en) Air-blast spray nozzle
DE1626114A1 (en) GAS TURBINE JET
DE899588C (en) Gas turbine, especially for pressurized aircraft cabins
DE1426423C3 (en) Gas turbine jet engine in three-flow and multi-shaft design
DE102009059019A1 (en) Arrangement for discharging oil-deaeration air in a gas turbine engine
DE1032033B (en) Ram air turbine as a power source for auxiliary equipment in a gas turbine aircraft
DE897634C (en) Exhaust gas turbine system for internal combustion engines with partial admission of the turbine blades
DE890257C (en) Jet machine
DE870281C (en) Method for operating shaft furnaces, in particular blast furnaces
DE918131C (en) Device for generating mechanical energy from the gases of jet propulsion with intermittently repeated combustion of air in tubes that are open on the one hand
CH246174A (en) Recoil engine for means of transport, in particular aircraft.
DE952852C (en) Gas turbine plant with pressure carburetor
CH229934A (en) Gas turbine plant.
DE1278183B (en) Pressurized gas starting device for a gas turbine jet engine
DE4324794C2 (en) Nozzle drive
DE466628C (en) Air heater in which the entire combustion air is introduced under pressure
DE582922C (en) Device for separating connected tobacco leaves
DE831580C (en) Device for conveying dusty gases by means of an axial blower
DE540734C (en) Grinding plant
DE1264871B (en) Gas turbine jet engine
DE1041740B (en) Device for starting gas turbine engines
DE532332C (en) Drying furnace for foundries
DE838007C (en) Vehicle driven by a gas turbine system, in particular a rail vehicle