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US 5,570,580 AGranted
Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle
AssigneeParker-Hannifin Corporation
InventorRobert T. Mains
Life of this patent
Estimating the term…
Abstract
A gas turbine fuel nozzle and method of fuel flow provide resistance to coking of the fuel by means of a multiple passage heat transfer cooling circuit. Fuel streams to primary and secondary sprays of pilot and main nozzle tips are arranged to transfer heat between the pilot primary fuel stream and each of the main secondary fuel stream and the pilot secondary fuel stream. This protects the fuel in the streams from coking during both low flow, lower engine heat conditions and high flow, high engine heat conditions. This nozzle and flow can protect engines with both single tip and dual tip nozzles.
Claims20
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a nozzle spray tip having a primary spray orifice through which fuel can be disposed for combustion and a secondary spray orifice through which fuel can be disposed for combustion, said secondary spray orifice surrounding said primary spray orifice;
- a primary fuel conduit connected to convey fuel to said primary spray orifice;
- and
- a secondary fuel conduit connected to convey fuel to said secondary spray orifice;
- said primary fuel conduit i) completely surrounds said secondary fuel conduit, ii) extends along at least a portion of the length of the secondary fuel conduit, and iii) is in a heat transfer relationship with said secondary fuel conduit.
2 more elements
A method of dispensing fuel in a gas turbine engine of the type having a nozzle tip from which fuel is sprayed into a combustor, comprising:
- providing a primary fuel conduit to the nozzle tip in adjoining heat transfer relationship with a secondary fuel conduit to the nozzle tip, said primary fuel conduit surrounding said secondary fuel conduit along at least a portion of the length of the secondary fuel conduit;
- continuously conveying fuel along the primary fuel conduit to the nozzle tip in a primary fuel stream when fuel is dispensed through the nozzle tip;
- conveying fuel along the secondary fuel conduit to the nozzle tip in a secondary fuel stream at a flow rate depending upon the fuel requirements for the gas turbine engine;
- and
- transferring heat between the primary fuel stream and the secondary fuel stream, and between the primary fuel conduit and the secondary fuel conduit.
2 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a first fuel spray nozzle disposed to spray fuel for combustion in the gas turbine engine;
- a second fuel spray nozzle disposed to spray fuel for combustion in the gas turbine engine;
- a first fuel conduit which extends within said first fuel spray nozzle to convey fuel to be sprayed therefrom;
- and
- a second fuel conduit separate from said first fuel conduit, a second portion of which extends in said second fuel spray nozzle to convey fuel to be sprayed therefrom and a first portion of which i) completely surrounds said first fuel conduit, ii) extends along at least a portion of said first fuel conduit, and iii) is in heat transfer relationship with said first fuel conduit.
2 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a nozzle spray tip having a primary spray orifice through which fuel can be disposed for combustion and a secondary spray orifice through which fuel can be disposed for combustion;
- a primary fuel conduit connected to convey fuel to said primary spray orifice;
- a secondary fuel conduit connected to convey fuel to said secondary spray orifice;
- said primary fuel conduit i) is coaxial with said secondary fuel conduit, ii) forms an annulus surrounding said secondary fuel conduit through which fuel can be conveyed to said nozzle spray tip, iii) completely surrounds said secondary fuel conduit, iv) extends along at least a portion of the length of the secondary fuel conduit, and v) is in a heat transfer relationship with said secondary fuel conduit, and
- heat transfer members extending radially outwardly from the secondary fuel conduit and interconnecting said primary fuel conduit and said secondary fuel conduit.
2 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a nozzle spray tip having a primary spray orifice through which fuel can be disposed for combustion and a secondary spray orifice through which fuel can be disposed for combustion;
- a primary fuel conduit connected to convey fuel to said primary spray orifice;
- and
- a secondary fuel conduit connected to convey fuel to said secondary spray orifice;
- said primary fuel conduit i) completely surrounds said secondary fuel conduit, ii) extends along at least a portion of the length of the secondary fuel conduit, and iii) is in a heat transfer relationship with said secondary fuel conduit, said secondary fuel conduit comprising an inner tube with a plurality of longitudinal webs extending radially outwardly therefrom, and said primary fuel conduit comprising an outer tube which mates with said webs of said inner tube to form interstitial spaces between said webs through which fuel can flow to said nozzle spray tip.
2 more elements
A method of dispensing fuel in a gas turbine engine of the type having a nozzle tip from which fuel is sprayed into a combustor, comprising:
- providing a primary fuel conduit to the nozzle tip in adjoining heat transfer relationship with a secondary fuel conduit to the nozzle tip, said primary fuel conduit surrounding said secondary fuel conduit along at least a portion of the length of the secondary fuel conduit;
- providing a plurality of longitudinal webs extending radially outward from the secondary fuel conduit to said primary fuel conduit to form interstitial spaces between said webs through which fuel can flow;
- conveying fuel along the primary fuel conduit to the nozzle tip in a primary fuel stream;
- conveying fuel along the secondary fuel conduit to the nozzle tip in a secondary fuel stream;
- and
- transferring heat between the primary fuel stream and the secondary fuel stream, between the primary fuel conduit and the secondary fuel conduit, and through said webs between said primary fuel conduit and said secondary fuel conduit.
3 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a first fuel spray nozzle disposed to spray fuel for combustion in the gas turbine engine;
- a second fuel spray nozzle disposed to spray fuel for combustion in the gas turbine engine;
- a first fuel conduit which extends within said first fuel spray nozzle to convey fuel to be sprayed therefrom;
- and
- a second fuel conduit separate from said first fuel conduit, a second portion of which extends in said second fuel spray nozzle to convey fuel to be sprayed therefrom and a first portion of which extends adjacent to and is intimately connected in a heat transfer relationship with said first fuel conduit,
- wherein said first fuel conduit is formed by a first tube through the interior of which fuel can flow to be sprayed from said first nozzle;
- and wherein said first portion of second fuel conduit is formed by a second tube i) completely surrounding said first tube;
- and ii) extending along at least a portion of the length of the first tube, and
- heat transfer members extend radially outwardly from said first tube and interconnect said first tube with said second tube.
6 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a nozzle spray tip having a spray orifice through which fuel can be disposed for combustion;
- a first fuel conduit connected to convey fuel to said nozzle spray tip;
- a second fuel conduit connected to convey fuel to said nozzle spray tip;
- said first fuel conduit completely surrounding said second fuel conduit and extending along at least a portion of the length of the second fuel conduit;
- and
- heat transfer web members extending outwardly from said second fuel conduit to said first fuel conduit and thermally interconnecting said first fuel conduit and said second fuel conduit for heat transfer therebetween.
3 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine comprising:
- a first spray nozzle having a spray orifice through which fuel can be disposed for combustion;
- a second spray nozzle having a spray orifice through which can be disposed for combustion;
- a first fuel tube and a second fuel tube combining first and second fuel conduits to said first and second spray nozzles, said first fuel tube (i) surround said second fuel tube, and (ii) extending along at least a portion of the length of the second fuel tube;
- and
- heat transfer members extending outwardly from said second fuel tube to said first fuel tube.
2 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a nozzle spray tip having a spray orifice through which fuel can be disposed for combustion;
- a first fuel conduit connected to convey fuel to said nozzle spray tip;
- a second fuel conduit connected to convey fuel to said nozzle spray tip;
- said first fuel conduit completely surrounding said second fuel conduit and extending along at least a portion of the length of the second fuel conduit;
- and
- heat transfer members extending outwardly from said second fuel conduit to said first fuel conduit and thermally interconnecting said first fuel conduit and said second fuel conduit for heat transfer therebetween, wherein said second fuel conduit comprises an inner tube and said heat transfer members comprise a plurality of longitudinal webs extending radially outward from said inner tube, and said first fuel conduit comprises an outer tube which mates with said webs of said inner tube to form interstitial spaces between said webs through which fuel can flow to said nozzle spray tip.
3 more elements
Dependencies are inferred from the claim text.