GB832557A - Improvements in or relating to rotor blades for gas turbines - Google Patents

Improvements in or relating to rotor blades for gas turbines

Info

Publication number
GB832557A
GB832557A GB1373457A GB1373457A GB832557A GB 832557 A GB832557 A GB 832557A GB 1373457 A GB1373457 A GB 1373457A GB 1373457 A GB1373457 A GB 1373457A GB 832557 A GB832557 A GB 832557A
Authority
GB
United Kingdom
Prior art keywords
blade
fuel
porous material
duct
tip
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
GB1373457A
Inventor
Johann Endres
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.)
Messerschmitt AG
Original Assignee
Messerschmitt AG
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 Messerschmitt AG filed Critical Messerschmitt AG
Priority to GB1373457A priority Critical patent/GB832557A/en
Publication of GB832557A publication Critical patent/GB832557A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/182—Transpiration cooling

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

832,557. Gas turbine rotor blades. MESSERSCHMITT A.G. April 30, 1957, No. 13734/57. Class 110 (3). In a surface-cooled rotor blade for gas turbines, the blade is hollow, is made of porous material and either has or has not an encasing wall perforated with outlet openings, the blade having a radially-disposed fuel delivery duct inside the porous material and the porous material having a density which increases and a porosity which diminishes radially towards the tip of the blade. The object of the invention is to obtain a cooled blade as well as uniformity of fuel discharge over the entire blade surface. The blade shown in Fig. 1 comprises a core 2 of porous material having a conical-shaped convergent fuel supply duct 3 within, fuel being supplied to the duct 3 through a passage 10 in the rotor shaft 7. An outer perforated casing 5 is disposed around the porous core 2 so that in operation a cooling layer 6 is formed on the outer surface of the blade. In a second embodiment, the outer perforated casing is not provided. The conical shape of the fuel duct 3 provides varying thicknesses of porous material so that fuel under greater pressure due to increased centrifugal force towards the blade tip has to flow through a greater thickness of less porous material. The subsequent combustion of the fuel in the gas stream has an inter-stage reheat effect and provides an approximately isothermal combustion process. Specification 619,634 is referred to.
GB1373457A 1957-04-30 1957-04-30 Improvements in or relating to rotor blades for gas turbines Expired GB832557A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1373457A GB832557A (en) 1957-04-30 1957-04-30 Improvements in or relating to rotor blades for gas turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1373457A GB832557A (en) 1957-04-30 1957-04-30 Improvements in or relating to rotor blades for gas turbines

Publications (1)

Publication Number Publication Date
GB832557A true GB832557A (en) 1960-04-13

Family

ID=10028391

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1373457A Expired GB832557A (en) 1957-04-30 1957-04-30 Improvements in or relating to rotor blades for gas turbines

Country Status (1)

Country Link
GB (1) GB832557A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112524641A (en) * 2020-12-02 2021-03-19 西北工业大学 Novel turbine interstage combustion chamber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112524641A (en) * 2020-12-02 2021-03-19 西北工业大学 Novel turbine interstage combustion chamber

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