Low emissions can combustor with dilution hole arrangement for a turbine engine

• US 6,101,814 A
• Filed: 04/15/1999
• Issued: 08/15/2000
• Est. Priority Date: 04/15/1999
• 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: Sonntag, Robert M., Olsen, Howard, Mountz, Daryl B., Hoke, James B.
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US09/292,136
• Time in Patent Office: 488 Days
• Field of Search: 60/752, 60/753, 60/754, 60/755, 60/756, 60/757, 60/758, 60/39.37, 60/742, 60/748
• US Class Current: 60/752
• CPC Class Codes: F23D 11/007 combination of means covered by sub-groups F23D11/10 and F23D11/24
• CPC Class Codes: F23D 2900/11002 Liquid fuel burners with more than one nozzle
• CPC Class Codes: F23D 2900/11101 Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers
• CPC Class Codes: F23R 2900/00016 Retrofitting in general, e.g. to respect new regulations on pollution
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A low emissions combustor can 18 for an aircraft gas turbine engine includes a louvered combustor liner 24 with three arrays of dilution holes 52, 54, 56. The first hole array comprises twelve equally sized, equiangularly distributed holes that penetrates the liner about midway along its axial length. The second hole array comprises twelve equally sized holes, smaller than the holes of the first array, that penetrate the liner a predetermined distance aft of the first hole array. The holes of the second array are equiangularly distributed and each second hole is circumferentially aligned with a first hole. A third hole array penetrates the liner a predefined distance aft of the first array. The third holes are nonuniformly sized and nonequiangularly distributed to regulate the spatial temperature profile of combustion gases exiting the combustor can. The quantity, size, distribution and location of the holes mitigates undesirable exhaust emissions without affecting the performance or durability of the engine. Accordingly, the combustor can may be used to replace an existing combustor can in an older generation gas turbine engine.

Claims

1. A combustor can for a turbine engine, comprising:

a liner comprising a set of eleven axially adjacent louvers, the liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a combustion zone and having an effective axial length;

a first array of dilution holes penetrating the liner about midway along the effective axial length of the liner and penetrating through the sixth of the eleven louvers;

a second array of dilution holes penetrating the liner a predetermined distance aft of the first array and penetrating through the seventh of the eleven louvers, each hole of the second hole array being substantially circumferentially aligned with a hole of the first hole array; and

a third array of dilution holes penetrating the liner aft of the second array and a predefined distance aft of the first array and penetrating through the tenth of the eleven louvers, the holes of the third array being nonequiangularly circumferentially distributed and irregularly sized.

6. A combustion chamber assembly comprising:

a combustor can as in claim 1 or 2; and

a fuel injector projecting into the combustor can, the fuel injector comprising;

a pressure atomizing core nozzle disposed about an injector centerline, the core nozzle having a discharge orifice for injecting a stream of primary fuel into a combustion zone of the module;

first and second partitions circumscribing the core nozzle to define radially inner and outer extremities of an annular inner air passage for injecting a stream of inner air into the combustion zone;

a third partition circumscribing the second partition and cooperating therewith to define a secondary fuel passage having an outlet oriented to direct a stream of secondary fuel into the combustion zone toward the injector centerline;

an outer wall circumscribing the third partition and forming the radially outermost border of an annular outer air passage having an outlet oriented to direct a stream of outer air into the combustion zone toward the injector centerline; and

an air distribution baffle having a cap with a plurality of air injection orifices extending therethrough, the cap extending radially across the inner air passage and having an outer edge radially spaced from the second partition to define an air injection annulus so that the cap divides the inner air stream into an annular substream that flows through the air injection annulus and a plurality of air jets that issue from the air injection orifices.

7. A retrofit kit for a gas turbine engine combustor module, comprising:

a combustor can as in claim 1 or 2; and

a fuel injector, comprising;

a pressure atomizing core nozzle disposed about an injector centerline, the core nozzle having a discharge orifice for injecting a stream of primary fuel into a combustion zone of the module;

first and second partitions circumscribing the core nozzle to define radially inner and outer extremities of an annular inner air passage for injecting a stream of inner air into the combustion zone;

a third partition circumscribing the second partition and cooperating therewith to define a secondary fuel passage having an outlet oriented to direct a stream of secondary fuel into the combustion zone toward the injector centerline;

an outer wall circumscribing the third partition and forming the radially outermost border of an annular outer air passage having an outlet oriented to direct a stream of outer air into the combustion zone toward the injector centerline; and

an air distribution baffle having a cap with a plurality of air injection orifices extending therethrough, the cap extending radially across the inner air passage and having an outer edge radially spaced from the second partition to define an air injection annulus so that the cap divides the inner air stream into an annular substream that flows through the air injection annulus and a plurality of air jets that issue from the air injection orifices.

8. A combustor module for a gas turbine engine, comprising:

an annular pressure vessel defined by inner and outer cases disposed about an axially extending module centerline;

a plurality of combustor cans as in claim 1 or 2, each can having an inner extremity and an outer extremity, the cans being equiangularly distributed within the pressure vessel annulus so that the inner extremities of the cans are equidistant from the module centerline, each can being secured to the outer case;

a plurality of fuel injectors secured to the outer case and each projecting through a fuel injector port, the fuel injector comprising;

a pressure atomizing core nozzle disposed about an injector centerline, the core nozzle having a discharge orifice for injecting a stream of primary fuel into a combustion zone of the module;

first and second partitions circumscribing the core nozzle to define radially inner and outer extremities of an annular inner air passage for injecting a stream of inner air into the combustion zone;

a third partition circumscribing the second partition and cooperating therewith to define a secondary fuel passage having an outlet oriented to direct a stream of secondary fuel into the combustion zone toward the injector centerline;

an outer wall circumscribing the third partition and forming the radially outermost border of an annular outer air passage having an outlet oriented to direct a stream of outer air into the combustion zone toward the injector centerline; and

an air distribution baffle having a cap with a plurality of air injection orifices extending therethrough, the cap extending radially across the inner air passage and having an outer edge radially spaced from the second partition to define an air injection annulus so that the cap divides the inner air stream into an annular substream that flows through the air injection annulus and a plurality of air jets that issue from the air injection orifices.

2. A combustor can for a turbine engine, comprising:

a liner with a centerline and a set of eleven axially adjacent louvers disposed about the liner centerline, the can having a forward end with a fuel injector port extending therethrough, the port being radially bordered by a fuel injector guide having a discharge opening, the can also having an aft end terminating at the trailing edge of the eleventh louver, the liner circumscribing a combustion zone and having an effective axial length;

a first array of equiangularly distributed circular dilution holes each having a common first diameter and penetrating the sixth louver;

a second array of equiangularly distributed circular dilution holes each having a common second diameter smaller than the first diameter and penetrating the seventh louver, each hole of the second hole array being substantially circumferentially aligned with a hole of the first hole array; and

a third array of nonequiangularly distributed circular dilution holes having nonuniform third diameters and penetrating the tenth louver.

3. The combustor can of claim 2, the can having radially inner and outer extremities and wherein the first and second hole arrays each comprise twelve holes, one hole of each array being positioned at the can outer extremity, and wherein the third hole array comprises ten holes angularly distributed as specified below:

space="preserve" listing-type="tabular">______________________________________ Hole Angular Offset ______________________________________ 1st 0°

2nd 10°

3rd 48°

4th 108°

5th 144°

6th 180°

7th 216°

8th 252°

9th 312°

10th 350°

______________________________________

where the first hole is at the can outer extremity and the second through tenth holes are clockwisely displaced from the first hole by the specified angular offset as viewed by an observer looking from the aft end of the liner toward the forward end of the liner.

4. The combustor can of claim 3 wherein the sixth, seventh and tenth louvers have diameters of about 7.0, 7.0 and 6.1 inches respectively, the holes of the first hole array have a diameter of about 0.640 inches, the holes of the second hole array have a diameter of about 0.425 inches, and the holes of the third hole array have diameters, expressed in inches, as specified below:

space="preserve" listing-type="tabular">______________________________________ Hole Diameter ______________________________________ 1st 0.400 2nd 0.150 3rd 0.865 4th 0.790 5th 0.250 6th 0.680 7th 0.250 8th 0.830 9th 0.965 10th 0.230. ______________________________________

5. The combustor can of claim 4 wherein the effective length of the can from the discharge opening of the fuel injector guide to the trailing edge of the eleventh louver is about 16.9 inches.

9. A combustor can for a turbine engine, comprising:

a liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a combustion zone and having an effective axial length and comprising a set of eleven axially adjacent louvers;

a first array of dilution holes penetrating the sixth of the eleven louvers about midway along the effective axial length of the liner;

a second array of dilution holes penetrating the seventh of the eleven louvers a predetermined distance aft of the first array, each hole of the second array being substantially circumferentially aligned with a hole of the first hole array; and

a third array of dilution holes penetrating the tenth of the eleven louvers a predefined distance aft of the first array, the holes of the third array being circumferentially distributed and sized so that a combustion gas stream issuing from the aft end of the liner exhibits a radial temperature profile that approximates a prescribed temperature profile.

10. A combustion chamber assembly comprising:

a combustor can comprising;

a liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a combustion zone and having an effective axial length;

a first array of dilution holes penetrating the liner about midway along the effective axial length of the liner;

a second array of dilution holes penetrating the liner a predetermined distance aft of the first array, each hole of the second hole array being substantially circumferentially aligned with a hole of the first hole array; and

a third array of dilution holes penetrating the liner aft of the second array and a predefined distance aft of the first array, the holes of the third array being circumferentially distributed and sized so that a combustion gas stream issuing from the aft end of the liner exhibits a radial temperature profile that approximates a prescribed temperature profile; and

a fuel injector projecting into the combustor can, the fuel injector comprising;

a pressure atomizing core nozzle disposed about an injector centerline, the core nozzle having a discharge orifice for injecting a stream of primary fuel into a combustion zone of the module;

first and second partitions circumscribing the core nozzle to define radially inner and outer extremities of an annular inner air passage for injecting a stream of inner air into the combustion zone;

a third partition circumscribing the second partition and cooperating therewith to define a secondary fuel passage having an outlet oriented to direct a stream of secondary fuel into the combustion zone toward the injector centerline;

an outer wall circumscribing the third partition and forming the radially outermost border of an annular outer air passage having an outlet oriented to direct a stream of outer air into the combustion zone toward the injector centerline; and

an air distribution baffle having a cap with a plurality of air injection orifices extending therethrough, the cap extending radially across the inner air passage and having an outer edge radially spaced from the second partition to define an air injection annulus so that the cap divides the inner air stream into an annular substream that flows through the air injection annulus and a plurality of air jets that issue from the air injection orifices.

11. A retrofit kit for a gas turbine engine combustor module, comprising:

a combustor can comprising;

a liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a combustion zone and having an effective axial length;

a first array of dilution holes penetrating the liner about midway along the effective axial length of the liner;

a second array of dilution holes penetrating the liner a predetermined distance aft of the first array, each hole of the second hole array being substantially circumferentially aligned with a hole of the first hole array; and

a third array of dilution holes penetrating the liner aft of the second array and a predefined distance aft of the first array, the holes of the third array being circumferentially distributed and sized so that a combustion gas stream issuing from the aft end of the liner exhibits a radial temperature profile that approximates a prescribed temperature profile; and

a fuel injector comprising;

a pressure atomizing core nozzle disposed about an injector centerline, the core nozzle having a discharge orifice for injecting a stream of primary fuel into a combustion zone of the module;

first and second partitions circumscribing the core nozzle to define radially inner and outer extremities of an annular inner air passage for injecting a stream of inner air into the combustion zone;

a third partition circumscribing the second partition and cooperating therewith to define a secondary fuel passage having an outlet oriented to direct a stream of secondary fuel into the combustion zone toward the injector centerline;

an outer wall circumscribing the third partition and forming the radially outermost border of an annular outer air passage having an outlet oriented to direct a stream of outer air into the combustion zone toward the injector centerline; and

an air distribution baffle having a cap with a plurality of air injection orifices extending therethrough, the cap extending radially across the inner air passage and having an outer edge radially spaced from the second partition to define an air injection annulus so that the cap divides the inner air stream into an annular substream that flows through the air injection annulus and a plurality of air jets that issue from the air injection orifices.

12. A combustor module for a gas turbine engine, comprising:

a) an annular pressure vessel defined by inner and outer cases disposed about an axially extending centerline;

b) a plurality of combustor cans, each can having an inner extremity and an outer extremity, the cans being equiangularly distributed within the pressure vessel annulus so that the inner extremities of the cans are equidistant from the module centerline, each can being secured to the outer case, each combustor can comprising;

a liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a combustion zone and having an effective axial length;

a first array of dilution holes penetrating the liner about midway along the effective axial length of the liner;

a second array of dilution holes penetrating the liner a predetermined distance aft of the first array, each hole of the second hole array being substantially circumferentially aligned with a hole of the first hole array; and

a third array of dilution holes penetrating the liner aft of the second array and a predefined distance aft of the first array, the holes of the third array being circumferentially distributed and sized so that a combustion gas stream issuing from the aft end of the liner exhibits a radial temperature profile that approximates a prescribed temperature profile; and

c) a plurality of fuel injectors, each secured to the outer case and each projecting into the combustor can through one of the fuel injector ports, each fuel injector comprising;

a pressure atomizing core nozzle disposed about an injector centerline, the core nozzle having a discharge orifice for injecting a stream of primary fuel into a combustion zone of the module;

first and second partitions circumscribing the core nozzle to define radially inner and outer extremities of an annular inner air passage for injecting a stream of inner air into the combustion zone;

a third partition circumscribing the second partition and cooperating therewith to define a secondary fuel passage having an outlet oriented to direct a stream of secondary fuel into the combustion zone toward the injector centerline;

an outer wall circumscribing the third partition and forming the radially outermost border of an annular outer air passage having an outlet oriented to direct a stream of outer air into the combustion zone toward the injector centerline; and

an air distribution baffle having a cap with a plurality of air injection orifices extending therethrough, the cap extending radially across the inner air passage and having an outer edge radially spaced from the second partition to define an air injection annulus so that the cap divides the inner air stream into an annular substream that flows through the air injection annulus and a plurality of air jets that issue from the air injection orifices.