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US 5,423,178 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.
Claims36
A method of dispensing fuel in a gas turbine engine of the type having pilot nozzle tips from which fuel is sprayed in primary and secondary sprays into a pilot zone of the combustor and main nozzle tips from which fuel is sprayed in primary and secondary sprays into a main zone of the combustor, comprising:
- conveying fuel to the primary spray of the main nozzle tip in a main primary fuel stream;
- conveying fuel to the secondary spray of the main nozzle tip in a main secondary fuel stream;
- conveying fuel to the primary spray of the pilot nozzle tip in a pilot primary fuel stream;
- conveying fuel to the secondary spray of the pilot nozzle tip in a pilot secondary fuel stream;
- transferring heat between fuel in said pilot primary fuel stream and fuel in said main secondary fuel stream;
- and
- transferring heat between fuel in said pilot secondary fuel stream and fuel in said pilot primary fuel stream.
4 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 extending about said first tube with longitudinal webs extending radially therebetween which mate with said first and second tubes to form interstitial spaces between said webs through which fuel can flow for heat transfer with fuel in said interior of said first tube.
4 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a first fuel conduit disposed in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- a second fuel conduit disposed in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- a third fuel conduit disposed in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- a fourth fuel conduit disposed in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- said third fuel conduit extends along and is intimately connected in a heat transfer relationship with said second fuel conduit and said fourth fuel conduit;
- and said third fuel conduit comprising a second conduit tube section and a fourth conduit tube section, said second conduit tube section comprising a webbed main inner tube with a plurality of longitudinal webs extending radially outwardly therefrom, and a main outer tube which mates with the said webs of said main inner tube to form interstitial spaces between said webs through which fuel can flow along said second fuel conduit for heat transfer.
3 more elements
A gas turbine fuel nozzle cooling circuit for a gas turbine engine, comprising:
- a first fuel conduit disposed in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- a second fuel conduit disposed in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- a third fuel conduit in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- a fourth fuel conduit in said engine and connected to convey fuel to be sprayed for combustion in said engine;
- a first nozzle spray tip to dispense fuel from said first and second fuel conduits, and a second nozzle spray tip to dispense fuel from said third and fourth fuel conduits;
- and
- said third fuel conduit extends along in adjoining relation and is intimately connected in a heat transfer relationship with said second fuel conduit, said fourth fuel conduit and said first nozzle spray tip.
4 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, surrounds at least a portion of, and is intimately connected in a heat transfer relationship with said first fuel spray nozzle and said first fuel conduit, and said second fuel conduit has a portion which directs fuel toward said first fuel spray nozzle, and a separate portion which directs fuel away from said first fuel spray nozzle.
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 extends adjacent to and is intimately connected in a heat transfer relationship with said first fuel conduit and said first fuel spray nozzle, said first portion of said second fuel conduit forming a first fluid path to direct fuel toward said first fuel spray nozzle and a second fluid path to direct fuel away from said first fuel spray nozzle.
2 more elements
A gas turbine fuel nozzle, comprising:
- a nozzle housing;
- a main nozzle spray tip connected to said housing and having a main primary spray orifice through which fuel can be dispersed for combustion and a main secondary spray orifice through which fuel can be dispersed for combustion;
- a pilot nozzle spray tip connected to said housing and having a pilot primary spray orifice through which fuel can be dispersed for combustion and a pilot secondary spray orifice through which fuel can be dispersed for combustion;
- a main primary fuel conduit disposed in said housing and connected to convey fuel to said main primary spray orifice;
- a main secondary fuel conduit disposed in said housing and connected to convey fuel to said main secondary spray orifice;
- a pilot primary fuel conduit disposed in said housing and connected to convey fuel to said pilot primary spray orifice;
- a pilot secondary fuel conduit disposed in said housing and connected to convey fuel to said pilot secondary spray orifice;
- and
- said pilot primary fuel conduit extends along and is intimately connected in a heat transfer relationship with said main secondary fuel conduit and said pilot secondary fuel conduit.
6 more elements
Dependencies are inferred from the claim text.