Durability flame stabilizing fuel injector with impingement and transpiration cooled tip

• US 6,178,752 B1
• Filed: 03/24/1998
• Issued: 01/30/2001
• Est. Priority Date: 03/24/1998
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Morford, Stephen A.
• Primary Examiner(s): Kim, Ted
• Application Number:
  US09/046,903
• Time in Patent Office: 1,043 Days
• Field of Search: 60/390.6, 607/37, 607/48, 607/57, 239/400, 239/403, 239/419, 239/419.3, 239/424.5, 431/173
• US Class Current: 60/737
• CPC Class Codes: F23C 2900/07002 Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
• CPC Class Codes: F23C 7/002 the air being submitted to a rotary or spinning motion cyclonic combustion chamber F23C3/006
• CPC Class Codes: F23D 14/02 Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
• CPC Class Codes: F23D 14/22 with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
• CPC Class Codes: F23D 14/78 Cooling burner parts
• CPC Class Codes: F23D 2204/00 Burners adapted for simultaneous or alternative combustion having more than one fuel supply
• CPC Class Codes: F23D 2900/14021 Premixing burners with swirling or vortices creating means for fuel or air

Abstract

The invention is a tangential entry, premixing fuel injector (10) for the combustion chamber (30) of a turbine engine. The injector includes a pair of arcuate scrolls (18) defining the radially outer boundary of a mixing chamber (28) and a pair of air entry slots (36) for admitting a stream of primary combustion air tangentially into the mixing chamber. The scrolls also include an axially distributed array of primary fuel injection passages (42) for injecting a primary fuel into the primary air stream. A flame stabilizing fuel injector centerbody (46) includes an impingement and transpiration cooled outlet nozzle (50) for introducing secondary fuel and secondary air into the combustion chamber. The nozzle (50) includes an impingement plate(74) with an array of impingement ports (76) and a tip cap (104) with an array of discharge passages (106). The impingement ports and discharge passages are in series flow, misaligned relationship so that secondary air exiting from the impingement ports impinges on the tip cap and flows through the core discharge passages to impingement cool and transpiration cool the nozzle. The disclosed injector runs cooler than a more conventional tangential entry injector and therefore is more durable. The improved durability is achieved even though the disclosed injector uses less cooling air than a more conventional tangential entry injector and discharges the cooling air at a lower velocity. The reduced cooling air quantity helps to minimize carbon monoxide emissions and the reduced discharge velocity improves the spatial and temporal stability of the combustion flame.

Claims

1. A fuel injector for a gas turbine engine combustion chamber, comprising:

at least two arcuate scrolls each having an axis substantially parallel to and radially offset from a fuel injector centerline, the scrolls defining the radially outer boundary of a mixing chamber, each adjacent pair of scrolls also defining an air entry slot for admitting a stream of primary combustion air into the mixing chamber, at least one of the scrolls including an axially distributed array of primary fuel injection passages for injecting a primary fuel into the primary air stream;

a centerbody comprising a centerbody base, a nozzle, and a shell extending axially from the base to the nozzle to define the radially inner boundary of the mixing chamber and the radially outer boundary of a secondary air supply conduit, the nozzle including;

a housing having a shroud portion;

a secondary air supply passageway for guiding a stream of secondary air into the interior of the housing;

an impingement plate circumscribed by the housing shroud so that the impingement plate intercepts the secondary air stream, the impingement plate having an array of impingement ports extending therethrough; and

a tip cap having an array of core discharge passages extending therethrough, the impingement ports and core discharge passages being in misaligned, series flow relationship so that secondary air exiting from the impingement ports impinges on the tip cap and flows through the core discharge passages to cool the nozzle.

2. The fuel injector of claim 1 wherein the secondary air experiences a first total pressure loss as it flows through the impingement ports and a second total pressure loss as it flows through the core discharge ports, the first pressure loss being larger than the second pressure loss so that the secondary air impinges on the tip cap at a first velocity and discharges from the core passages at a second velocity, the first velocity being higher than the second velocity.

3. The fuel injector of claim 2 wherein the first pressure loss is at least about four times as great as the second pressure loss.

4. The fuel injector of claim 1, comprising:

a fuel distribution chamber for receiving and spatially distributing a stream of secondary fuel;

a secondary fuel manifold spaced from the fuel distribution chamber by an orifice plate, the orifice plate having an array of orifices for establishing fluid communication between the distribution chamber and the manifold; and

an array of perimeter fuel discharge passages extending from the fuel manifold and through the housing for injecting the secondary fuel into the combustion chamber.

5. The fuel injector of claim 4 wherein the housing includes a radially enlarged rim portion with an array of perimeter air discharge passages extending therethrough, each perimeter air discharge passage having an inlet end in communication with the secondary air supply conduit and an outlet end in communication with the combustion chamber, the perimeter air passages being interspersed with the perimeter fuel discharge passages.

6. The fuel injector of claim 4 wherein the secondary fuel is a gaseous fuel.

7. The fuel injector of claim 1, comprising:

an insert nested within the housing, the insert having a hub with a central opening that serves as the secondary air supply passageway, an orifice plate extending between the hub and the housing and having an array of orifices therethrough, and a hub extension also extending from the hub to the housing;

a plug nested radially between the hub and the housing and axially spaced from the orifice plate, the plug including an aperture for receiving a secondary fuel supply tube that introduces secondary fuel into the nozzle;

the plug, the insert and the housing cooperating to define an annular fuel distribution chamber and a fuel manifold with the orifices extending between the chamber and the manifold;

the housing having an array of perimeter fuel discharge passages extending from the fuel manifold and through the housing for injecting the secondary fuel into the combustion chamber.

8. The fuel injector of claim 7 wherein the housing includes a radially enlarged rim portion with an array of perimeter air discharge passages extending therethrough, each perimeter air discharge passage having an inlet end in communication with the secondary air supply conduit and an outlet end in communication with the combustion chamber, the perimeter air passages being interspersed with the perimeter fuel discharge passages.

9. The fuel injector of claim 7 wherein the secondary fuel is a gaseous fuel.

10. The fuel injector of claim 1 wherein the core passages are substantially parallel to the fuel injector centerline.

11. A nozzle assembly for a fuel injector, comprising:

a housing with a shroud portion having a forward end and an aft end, the aft end being a radially enlarged rim having an array of perimeter air discharge passages and an array of perimeter fuel discharge passages extending therethrough, the housing also including an impingement plate circumscribed by the shroud with an array of impingement ports extending through the impingement plate;

an insert, coaxial with the housing and circumscribed thereby, the insert including a hub, an orifice plate projecting from the hub to the housing, the orifice plate including an array of orifices, and an aftwardly diverging hub extension also projecting from the hub to the housing;

the housing, the orifice plate and the hub extension defining an annular fuel manifold in communication with the perimeter fuel discharge passages, the hub including a central opening that defines a secondary air supply passageway for admitting secondary air into the nozzle;

a plug nested radially between the hub and the housing and having an aperture for receiving a fuel supply tube for introducing secondary fuel into the nozzle;

the plug, the orifice plate, the hub and the housing defining a fuel distribution chamber connected to the fuel manifold by the orifices; and

a tip cap circumscribed by the aft end of the housing and axially spaced from the impingement plate to define an air distribution chamber, the tip cap including an array of core air discharge passages, the core discharge passages and impingement ports being in misaligned, series flow relationship so that secondary air exiting from the impingement ports impinges on the tip cap and flows through the core discharge passages to cool the nozzle.