Pilot arrangement, nozzle device, production method, and gas turbine arrangement

Abstract

A pilot arrangement for use in a nozzle device of a gas turbine includes a cavity, extending along a longitudinal axis, for conducting fuel, the narrowest flow cross section of which is larger than the largest flow cross section of a pilot line of a pilot fuel nozzle. The pilot fuel nozzle, adjoining the cavity in a downstream direction includes the pilot line and a pilot fuel outlet arranged at the downstream end of the pilot line. The cavity is arranged in a central body arranged on the axis, and at least one swirling element is arranged circumferentially around the central body. The central body and the swirling element form a swirling arrangement. Manufacturing advantages are achieved in that the pilot arrangement is made up of two components, wherein a first component includes the swirling element and the central body, and a second component includes the pilot fuel nozzle.

1 . A pilot arrangement for use in a nozzle device of a gas turbine arrangement, in particular of an aircraft engine, comprising
 a cavity, extending along a longitudinal axis, for conducting fuel, the narrowest flow cross section of which is larger than the largest flow cross section of a pilot line of a pilot fuel nozzle, and   the pilot fuel nozzle, which adjoins the cavity in a downstream direction and comprises the pilot line and a pilot fuel outlet arranged at the downstream end of the pilot line,   wherein the cavity is arranged in a central body arranged on the longitudinal axis, and wherein at least one swirling element is arranged circumferentially around the central body, wherein the central body and the at least one swirling element form a swirling arrangement, wherein the pilot arrangement is made up of two components, wherein a first component comprises the at least one swirling element and the central body, and a second component comprises the pilot fuel nozzle.   
     
     
         2 . The pilot arrangement according to  claim 1 , wherein the first component is in the form of a cohesive, integral component. 
     
     
         3 . The pilot arrangement according to  claim 1 , wherein the first component has at least one pilot fuel supply line for supplying fuel into the cavity, wherein the at least one pilot fuel supply line passes through the at least one swirling element in order to conduct pilot fuel from a circumferential wall of an inner air channel radially inwardly into the cavity. 
     
     
         4 . The pilot arrangement according to  claim 3 , wherein the first component has at least five and at most eight swirling elements. 
     
     
         5 . The pilot arrangement according to  claim 1 , wherein the second component comprises a sleeve, in particular a ceramic sleeve, arranged circumferentially around the pilot line. 
     
     
         6 . The pilot arrangement according to  claim 5 , wherein the second component has a separating element, in particular a sealing separating element, arranged between the upstream end of the sleeve and the cavity. 
     
     
         7 . The pilot arrangement according to  claim 1 , wherein the second component comprises a lance which extends along the longitudinal axis and accommodates the pilot line and/or the sleeve and/or the separating element, wherein the lance comprising the pilot line has an axial length such that the fuel outlet is positioned at least in a downstream third or quarter, preferably at least substantially at an outlet, of an inner air channel of the nozzle device. 
     
     
         8 . The pilot arrangement according to  claim 1 , wherein the pilot line tapers towards a pilot fuel outlet by means of a narrowing. 
     
     
         9 . The pilot arrangement according to  claim 8 , wherein the narrowing is formed by means of a tubular element which is arranged in and/or downstream of a line element of the pilot line and has a smaller flow cross section than the line element. 
     
     
         10 . The pilot arrangement according to  claim 1 , wherein the flow cross section(s) of the pilot line and/or of the at least one pilot fuel supply line is/are round. 
     
     
         11 . A nozzle device comprising a pilot arrangement according to  claim 1  and comprising an inner air channel, which is arranged on a longitudinal axis of the nozzle device and within which the pilot arrangement is arranged coaxially with the inner air channel. 
     
     
         12 . A method for producing a pilot arrangement which is designed according to  claim 1 , comprising the steps of:
 c. providing a first component comprising at least one swirling element and a central body, and a second component comprising a pilot fuel nozzle;   d. fastening the two components together by joining, for example brazing or welding.   
     
     
         13 . The method according to  claim 12 , wherein to provide the first component, said first component is manufactured, in particular integrally, by means of milling, drilling and/or turning processes. 
     
     
         14 . The method according to  claim 12 , wherein to provide the second component, said second component is preassembled, wherein
 for example a tubular element is fastened, in particular brazed in, at a downstream end of a line element comprising a pilot line coaxial with the line element as the downstream end of the pilot line;   a sleeve is introduced from an upstream end of a lance into an elongate interior of the latter;   the line element comprising a separating element and optionally the tubular element is introduced into the sleeve and is fixed to the tip of the lance, for example by means of brazing.   
     
     
         15 . A gas turbine arrangement, in particular for an aircraft, comprising a combustion chamber arrangement comprising at least one nozzle device according to  claim 11  and a turbine arrangement.