Turbine engine with engine core and outlet air duct

Abstract

The invention relates to a turbine engine having an engine core and an outlet air duct. A turbine engine has an engine core, a fan section, an outlet air duct, and an exhaust assembly. The engine core has a compressor section, a combustor section, and a turbine section arranged in series flow and defining a stator, a rotor, and a fire zone. The fan section is rotationally coupled to the rotor. The outlet air duct is fluidly coupled to at least one of the fan section or the compressor section and has a gravity low point within the fire region. A discharge assembly is disposed along the outlet air conduit.

Description

Technical Field

[0001] The present disclosure generally relates to a turbine engine having an engine core, and more particularly to an air bleed duct of a turbine engine. Background Art

[0002] Turbine engines and particularly gas or combustion turbine engines include a compressor section, a combustion section, and a turbine section, which define an engine core. A turbine engine is a rotary engine that extracts energy from a gas flow that passes through a fan section having a plurality of fan blades and then into a compressor section having pairs of rotating blades and stationary guide vanes, through a combustion section, and then through a turbine section having pairs of rotating blades and stationary guide vanes. The blades are mounted to rotating disks, while the guide vanes are mounted to stator disks. The compressor section, the combustion section, and the turbine section are collectively referred to as the engine core. In accordance with Part 25 of 14 CFR, at least portions of the engine core are classified as designated fire zones. As used herein, a "(plural) fire zone" is an area or compartment of a turbine engine that is outside the engine core but vulnerable to fire (if ignition were to occur in that zone). Turbine engines include additional designated zones, such as a "flammable fluid leakage zone" (FFLZ). The FFLZ is a portion of the turbine engine that has been shown to be free of ignition sources for flammable fluids during operation of the turbine engine (e.g., during flight, takeoff, failure, etc.). It will be recognized that the FFLZ is outside the fire zone.

[0003] Bleed air is drawn from an upstream section of the turbine engine (e.g., the fan section, the compressor section, or a combination thereof) and supplied to a downstream section of the turbine engine or an auxiliary system of the turbine engine. Bleed air can be drawn from a section of the turbine engine to determine the pressure, velocity, temperature, or a combination thereof of the working air flow passing through the corresponding portion of the turbine engine from which the bleed air is drawn. An engine controller can be used to control the supply of bleed air or otherwise measure the temperature, velocity, pressure, or a combination thereof of the bleed air. Summary of the Invention

[0004] Technical Solution 1. A turbine engine, comprising:

[0005] An engine core including a compressor section, a burner section, and a turbine section arranged in a series flow configuration and defining a stator, a rotor, and a fire zone;

[0006] A fan section rotatably coupled to the rotor;

[0007] An air bleed duct fluidly coupled to at least one of the fan section or the compressor section and having a gravity low point within the fire zone; and

[0008] A discharge assembly is disposed at a joint along the outlet air duct. The discharge assembly includes a bleed hole fluidly connected to the gravity low point, and a discharge duct fluidly connected to the bleed hole and having an outlet outside the fire area.

[0009] Technical solution 2. The turbine engine according to any of the foregoing technical solutions, wherein the discharge assembly includes a joint fitting, and the joint fitting includes the joint.

[0010] Technical solution 3. The turbine engine according to any of the foregoing technical solutions, wherein at least a part of the bleed hole is formed within the joint fitting.

[0011] Technical solution 4. The turbine engine according to any of the foregoing technical solutions, wherein the bleed hole is disposed within a bleed hole fitting connected to the joint fitting.

[0012] Technical solution 5. The turbine engine according to any of the foregoing technical solutions, wherein the discharge duct is connected to the joint fitting by at least one of welding, bonding, fastening, threaded connection, or a combination thereof.

[0013] Technical solution 6. The turbine engine according to any of the foregoing technical solutions, wherein the joint fitting is welded to the outlet air duct.

[0014] Technical solution 7. The turbine engine according to any of the foregoing technical solutions, wherein the joint fitting includes a top portion and a stem portion. The top portion includes a first internal passage, and the stem portion includes a second internal passage fluidly connected to the first internal passage at the joint. The top portion extends transversely to the stem portion.

[0015] Technical solution 8. The turbine engine according to any of the foregoing technical solutions, wherein at least one outlet air duct is at least partially defined by the first internal passage.

[0016] Technical solution 9. The turbine engine according to any of the foregoing technical solutions, wherein the bleed hole is disposed within the fire area.

[0017] Technical solution 10. The turbine engine according to any of the foregoing technical solutions, wherein the bleed hole is disposed outside the fire area.

[0018] Technical solution 11. The turbine engine according to any of the foregoing technical solutions, further includes a bleed hole fitting, and wherein the bleed hole fitting defines the outlet of the discharge duct.

[0019] Aspect 12. The turbine engine according to any of the foregoing aspects further includes a combustible fluid leakage zone (FFLZ) and an engine controller. The bleed air duct extends into the FFLZ. The engine controller is disposed within the FFLZ and is operably coupled to the bleed air duct.

[0020] Aspect 13. The turbine engine according to any of the foregoing aspects, wherein the engine controller is operably coupled to the bleed air duct downstream of the fluid at the joint.

[0021] Aspect 14. The turbine engine according to any of the foregoing aspects, wherein the engine controller measures at least one of the temperature, pressure, or a combination thereof of the bleed air flow within the bleed air duct to determine at least one of the pressure, temperature, or a combination thereof of the working air flow from the region of the turbine engine from which the bleed air flow within the bleed air duct is drawn.

[0022] Aspect 15. The turbine engine according to any of the foregoing aspects, wherein the engine controller is a full-authority digital engine controller (FADEC).

[0023] Aspect 16. The turbine engine according to any of the foregoing aspects, wherein the emission assembly is included within a plurality of emission assemblies, and the bleed air duct is included within a plurality of bleed air ducts.

[0024] Aspect 17. The turbine engine according to any of the foregoing aspects, wherein at least one of the plurality of emission assemblies is fluidly coupled to two or more of the plurality of bleed air ducts.

[0025] Aspect 18. The turbine engine according to any of the foregoing aspects, wherein the emission assembly is fluidly coupled to the bleed air duct at two or more joints along the bleed air duct.

[0026] Aspect 19. The turbine engine according to any of the foregoing aspects further includes a nacelle surrounding the engine core, wherein the discharge duct discharges to the outside of the nacelle.

[0027] Aspect 20. The turbine engine according to any of the foregoing aspects, wherein the fan section includes a plurality of fan blades extending outward from the nacelle. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] A complete and enabling disclosure of the present disclosure (including its best mode) for a person of ordinary skill in the art is set forth in the specification, with reference to the accompanying drawings, in which:

[0029] Figure 1 is a schematic cross-sectional view of a ducted-fanless turbine engine including a group of bleed air ducts and a group of discharge assemblies, according to an exemplary embodiment of the present disclosure.

[0030] Figure 2 is a schematic illustration of a discharge assembly fluidly coupled to a bleed air duct adapted for use in a Figure 1 ducted-fanless turbine engine, the discharge assembly having a discharge duct, a fitting, and a bleed hole fitting coupled to the fitting.

[0031] Figure 3 is Figure 3 a schematic representation of a bleed air duct further illustrating a plurality of discharge assemblies.

[0032] Figure 4 is a schematic illustration of an exemplary discharge assembly fluidly coupled to a bleed air duct adapted for use in a Figure 1 ducted-fanless turbine engine, the exemplary discharge assembly having a discharge duct, a fitting having a bleed hole.

[0033] Figure 5 is a schematic illustration of an exemplary discharge assembly fluidly coupled to a bleed air duct adapted for use in a Figure 1 ducted-fanless turbine engine, the exemplary discharge assembly having a discharge duct, a fitting, and a bleed hole fitting threadably coupled to the fitting.

[0034] Figure 6 is a schematic illustration of an exemplary discharge assembly fluidly coupled to a bleed air duct adapted for use in a Figure 1 ducted-fanless turbine engine, the exemplary discharge assembly having a discharge duct, a fitting, and a bleed hole fitting defining an outlet of the discharge assembly.

[0035] Figure 7 is a schematic illustration of an exemplary discharge assembly fluidly coupled to a bleed air duct adapted for use in a Figure 1 ducted-fanless turbine engine, the exemplary discharge assembly having a discharge duct, a fitting, and a bleed hole formed by both the discharge duct and the fitting.

[0036] Figure 8 is a schematic illustration of an exemplary discharge assembly fluidly coupled to a bleed air duct adapted for use in a Figure 1 ducted-fanless turbine engine, the exemplary discharge assembly having a discharge duct, a fitting, a bleed hole, a lip, and a seat.

[0037] Figure 9 is a schematic illustration of an exemplary discharge assembly fluidly coupled to a bleed air duct adapted for use in a Figure 1Schematic illustration of an exemplary drain assembly for a bleed air duct used in a ducted fanless turbine engine, the exemplary drain assembly having a drain duct, a fitting, and a weep hole fitting threadedly connected to the drain duct and the fitting.

[0038] Figure 10 is fluidly coupled to an exemplary drain assembly for a bleed air duct adapted for use in Figure 1 Schematic illustration of an exemplary drain assembly for a bleed air duct used in a ducted fanless turbine engine, the exemplary drain assembly having a drain duct, a fitting, and a weep hole fitting, the fitting and the weep hole fitting forming a Y-joint. DETAILED DESCRIPTION

[0039] Aspects of the present disclosure are directed to a turbine engine having a fire zone and a FFLZ. The turbine engine has an engine controller, a bleed air duct, and a drain assembly. The engine controller is configured to measure at least one of a flow rate (e.g., velocity) of the bleed air flow within the bleed air duct, a temperature of the bleed air flow within the bleed air duct, a pressure of the bleed air flow within the bleed air duct, or a combination thereof. The drain assembly includes a drain duct, a weep hole, and a fitting. As used herein, the term "fitting" refers to a physical component including a body that defines at least one internal passage extending through the body. The drain assembly is disposed along the bleed air duct. The fitting fluidly couples the drain duct to the bleed air duct.

[0040] At least a portion of the drain assembly is disposed within the fire zone of the turbine engine. The engine controller is disposed within the FFLZ. The drain assembly collects moisture (e.g., condensate) from within the bleed air duct. The collected moisture is then discharged through the drain assembly outside of the fire zone and out of the fire zone. The moisture is collected before the bleed air enters the FFLZ. Specifically, the moisture is collected before the bleed air enters the location where the engine controller is coupled (e.g., via a sensor) to the bleed air duct within the FFLZ. For illustrative purposes, the present disclosure will be described with respect to a drain assembly for a turbine engine (specifically, a ducted fanless turbine engine). However, it will be understood that aspects of the present disclosure described herein are not so limited and may have general applicability within other engines or within other portions of a turbine engine. For example, the present disclosure may be applicable to drain assemblies in other engines or vehicles and may be used to provide benefits in industrial, commercial, and residential applications.

[0041] As used herein, the "fire zone" of a turbine engine refers to the legally designated area of the turbine engine that requires a system for detecting and differentiating fire. The fire zone can include various systems or components that, if exposed to undetected fire, can cause failure of the turbine engine. An "undetected fire" is an accidental or undesired fire that is not differentiated or otherwise reduced by the system for detecting and differentiating fire. The fire zone can include, for example, the engine core of the turbine engine, the accessory power unit of the turbine engine, any fuel combustion heaters or accessories in the combustion section, and any pipelines carrying combustible fuel or gas.

[0042] As used herein, the "FFLZ" of a turbine engine refers to the legally designated area of the turbine engine that does not include an ignition source. The ignition source can include, for example, an igniter. It will be appreciated that the FFLZ is an area where both electrical equipment (e.g., engine controllers, sensors, wires, etc.) and combustible liquid pipelines (e.g., bleed air ducts, fuel pipelines, etc.) overlap. Specifically, the engine controller includes sensors that are coupled to corresponding portions of the combustible liquid pipelines within the FFLZ to measure at least one of the pressure, temperature, or velocity of the liquid within the combustible liquid pipelines. The FFLZ is so designated to ensure that if a leak of combustible liquid from the combustible liquid pipelines does occur within the FFLZ, ignition of the combustible liquid will not occur because there is no ignition source within the FFLZ.

[0043] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, and the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "front" or "forward" mean in front of something, and "back" or "rear" mean behind something. For example, when used in the context of fluid flow, front / forward can mean upstream, and back / rear can mean downstream.

[0044] Additionally, as used herein, both the terms "axial" and "longitudinal" refer to the direction parallel to the centerline axis of an object, while the term "radial" or "radially" refers to the direction perpendicular to the axial direction or away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the central longitudinal axis of the engine and the outer circumference of the engine. Further, as used herein, the term "group" or "groups" of elements can be any number of elements, including only one.

[0045] In addition, as used herein, the term "fluid" or its iterations may refer to any suitable fluid within a gas turbine engine to which at least a portion of the gas turbine engine is exposed, such as but not limited to combustion gases, ambient air, pressurized air streams, working air streams, or any combination thereof. It is further contemplated that the gas turbine engine may be another suitable turbine engine, such as but not limited to a steam turbine engine or a supercritical carbon dioxide turbine engine. By way of non-limiting example, the term "fluid" may refer to steam in a steam turbine engine or carbon dioxide in a supercritical carbon dioxide turbine engine.

[0046] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are for identification purposes only to assist the reader in understanding the present disclosure and do not form a limitation, particularly as to the position, orientation, or use of aspects of the present disclosure described herein. Connecting references (e.g., attached, coupled, fixed, fastened, connected, and joined) are to be construed broadly and may include intermediate members between a series of elements and relative movement between the elements, unless otherwise indicated. Thus, a connecting reference does not necessarily imply that the two elements are directly connected to each other and in a fixed relationship. Exemplary drawings are for illustrative purposes only, and the dimensions, positions, orders, and relative sizes reflected in the drawings attached hereto may vary.

[0047] As used herein, a "system" or "controller module" may include at least one processor and a memory. Non-limiting examples of the memory may include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memories, such as optical discs, digital versatile discs (DVDs), compact disc-read only memory (CD-ROMs), etc., or any suitable combination of these types of memories. The processor may be configured to run any suitable program or executable instructions designed to perform various methods, functions, processing tasks, calculations, etc. to permit or effectuate the technical operations or actions described herein. The program may include a computer program product that may include a machine-readable medium for carrying or having stored thereon machine-executable instructions or data structures. Such a machine-readable medium may be any available medium accessible by a general-purpose or special-purpose computer or other machine having a processor. Generally, such a computer program may include routines, programs, objects, components, data structures, algorithms, etc. that have the technical effect of performing a particular task or implementing a particular abstract data type.

[0048] Figure 1is a schematic cross-sectional view of a turbomachine (specifically, an open rotor or ducted fan engine 10 for an aircraft). The ducted fan engine 10 has a generally longitudinally extending axis or engine centerline 12 that extends from a front end 14 to a rear end 16. The ducted fan engine 10 includes, in a downstream series flow relationship, a group of circumferentially spaced blades or propellers that define a fan section 18 including a fan 20, a compressor section 22 including a booster or low pressure (LP) compressor 24 and a high pressure (HP) compressor 26, a combustion section 28 including a burner 30, a turbine section 32 including an HP turbine 34 and an LP turbine 36, and an exhaust section 38. The ducted fan engine 10 described herein is intended as a non-limiting example, and other architectures are possible, such as but not limited to steam turbine engines, supercritical carbon dioxide turbine engines, or any other suitable turbomachine.

[0049] The outer surface of the ducted fan engine 10 defined by a casing or nacelle 40 extends from the front end 14 of the ducted fan engine 10 toward the rear end 16 of the ducted fan engine 10 and covers at least a portion of the compressor section 22, the combustion section 28, the turbine section 32, and the exhaust section 38. The fan section 18 may be positioned at a front portion of the nacelle 40 and extends radially outward from the nacelle 40 of the ducted fan engine 10. Specifically, the fan section 18 extends radially outward from the nacelle 40. The fan section 18 includes a group of fan blades 42 and a group of fan guide vanes 82 downstream of the group of fan blades 42, both of which are radially disposed from the engine centerline 12 and circumferentially disposed about the engine centerline 12. The group of fan blades 42 and the group of fan guide vanes 82 extend radially outward from corresponding portions of the nacelle 40. Thus, the group of fan blades 42 and the group of fan guide vanes 82 may be defined as an outer group of fan blades and an outer group of fan guide vanes 82, respectively. The ducted fan engine 10 includes any number of one or more groups of rotating blades or propellers (e.g., the group of fan blades 42) that are disposed upstream of the group of fan guide vanes 82. As a non-limiting example, the ducted fan engine 10 may include multiple groups of fan blades 4 or stationary fan guide vanes 82. Thus, the ducted fan engine 10 is further defined as a ducted single fan turbomachine. The ducted fan engine 10 is further defined by the position of the fan section 18 relative to the combustion section 28. The fan section 18 may be upstream of, downstream of, or axially aligned with the combustion section 28.

[0050] The compressor section 22, the combustion section 28, and the turbine section 32 are collectively referred to as the engine core 44, which generates combustion gases. The engine core 44 is surrounded by an engine casing 46 that is operatively coupled to a portion of the nacelle 40 of the ducted fan engine 10.

[0051] The HP shaft 48, which is coaxially arranged about the engine centerline 12 of the ducted fanless turbine engine 10, drivingly connects the HP turbine 34 to the HP compressor 26. The LP shaft 50, which is coaxially arranged within the larger diameter annular HP shaft 48 about the engine centerline 12 of the ducted fanless turbine engine 10, drivingly connects the LP turbine 36 to the LP compressor 24 and the fan 20. The HP shaft 48 and the LP shaft 50 are rotatable about the engine centerline 12 and are connected to a set of rotatable elements, which together define the rotor 51.

[0052] It will be appreciated that the ducted fanless turbine engine 10 is a direct drive engine or an integrated drive engine that utilizes a reduction gearbox that connects the LP shaft 50 to the fan 20.

[0053] The LP compressor 24 and the HP compressor 26 each include a set of compressor stages 52, 54, wherein the set of compressor blades 56, 58 rotate relative to the corresponding set of stationary compressor guide vanes 60, 62 (also referred to as nozzles) to compress or pressurize the fluid flow passing through the stage. In a single compressor stage 52, 54, a plurality of compressor blades 56, 58 are arranged in a ring and extend radially outward from the blade platform to the blade tip relative to the engine centerline 12, while the corresponding stationary compressor guide vanes 60, 62 are positioned upstream and adjacent to the compressor blades 56, 58. Note that Figure 1 the number of blades, guide vanes, and compressor stages shown is chosen for illustrative purposes only, and other numbers are possible.

[0054] The compressor blades 56, 58 for the stages of the compressor section 22 are mounted to disks 61, which are mounted to the corresponding one of the HP shaft 48 and the LP shaft 50, wherein each stage has its own disk 61. The stationary compressor guide vanes 60, 62 for the stages of the compressor section 22 are mounted to the engine casing 46 in a circumferential arrangement.

[0055] The HP turbine 34 and the LP turbine 36 each include a set of turbine stages 64, 66, wherein the set of turbine blades 68, 70 rotate relative to the corresponding set of stationary turbine guide vanes 72, 74 (also referred to as nozzles) to extract energy from the fluid flow passing through the stage. In a single turbine stage 64, 66, a plurality of turbine blades 68, 70 are arranged in a ring and extend radially outward from the blade platform to the blade tip relative to the engine centerline 12, while the corresponding stationary turbine guide vanes 72, 74 are positioned upstream and adjacent to the turbine blades 68, 70. Note that Figure 1 the number of blades, guide vanes, and turbine stages shown is chosen for illustrative purposes only, and other numbers are possible.

[0056] The turbine blades 68, 70 for the stages of the turbine section 32 are mounted to a disk 71, which is mounted to a corresponding one of the HP shaft 48 and the LP shaft 50, where each stage has a dedicated disk 71. The static turbine guide vanes 72, 74 for the stages of the turbine section 32 are mounted to the engine casing 46 in a circumferential arrangement.

[0057] The rotating parts of the ducted fan engine 10, such as the blades 56, 58, 68, 70 in the compressor section 22 and the turbine section 32, are also referred to individually or collectively as the rotor 51. Thus, the rotor 51 refers to the combination of rotating elements throughout the ducted fan engine 10.

[0058] Complementary to the rotating parts, the stationary parts of the ducted fan engine 10, such as the static guide vanes 60, 62, 72, 74 in the compressor section 22 and the turbine section 32, are also referred to individually or collectively as the stator 63. Thus, the stator 63 refers to the combination of non-rotating elements throughout the ducted fan engine 10.

[0059] The nacelle 40 is operatively coupled to the ducted fan engine 10 and covers at least part of the engine core 44, the engine casing 46, or the exhaust section 38. At least part of the nacelle 40 extends axially forward or upstream from the illustrated position. For example, the nacelle 40 extends axially forward such that a portion of the nacelle 40 covers or overlies a portion of the fan section 18 or the supercharger section (not illustrated) of the ducted fan engine 10.

[0060] It will be appreciated that the ducted fan engine 10 can be divided into at least two separate parts: a rotor part and a stator part. The rotor part can be defined as any part of the ducted fan engine 10 that rotates about a corresponding axis of rotation. The stator part can be defined by the combination of non-rotating elements disposed within the ducted fan engine 10. By way of non-limiting example, the rotor part can include the plurality of fan blades 42, the compressor blades 56, 58, or the turbine blades 68, 70. By way of non-limiting example, the stator part can include the plurality of fan guide vanes 82, the static compressor guide vanes 60, 62, or the static turbine guide vanes 72, 74.

[0061] The ducted fan engine 10 is divided into zones, which are designated by the risk of fire occurring in the zones. By way of non-limiting example, the ducted fan engine 10 includes a fire zone 118, which includes at least the engine core 44. The ducted fan engine 10 includes a FFLZ 164. Although illustrated as being external to the engine core 44, it will be appreciated that the FFLZ 164 is disposed in any suitable region of the ducted fan engine 10. By way of non-limiting example, the FFLZ 164 includes the engine casing 46.

[0062] The ducted-fanless turbine engine 10 includes an engine controller 112 having a processor and a memory. The engine controller 112 or the processor can be operably or communicatively coupled to various parts of the ducted-fanless turbine engine 10 and is configured to operate the various parts. As a non-limiting example, the engine controller 112 can include sensors 114. The sensors 114 are used to measure at least one of pressure, velocity, temperature, or a combination thereof of the fluid flow within the corresponding parts of the ducted-fanless turbine engine 10. The engine controller 112 can control the corresponding parts of the ducted-fanless turbine engine 10 based on the measurements from the sensors 114.

[0063] The engine controller 112 is disposed within the FFLZ 164. It is contemplated that the placement of the engine controller 112 is selected to avoid overheating the engine controller 112. Specifically, during operation of the ducted-fanless turbine engine 10, the engine core 44 generates heat through compression of the working air flow within the ducted-fanless turbine engine 10 and combustion of the gas. If the engine controller 112 is exposed to heat, the heat generated by the operation of the ducted-fanless turbine engine 10 can damage the engine controller 112 in some cases. Positioning the engine controller 112 within the FFLZ 164 and outside the fire zone 118 places the engine controller 112 in a location where heat from the ducted-fanless turbine engine 10 will not overheat and damage the engine controller 112. The engine controller 112 can be any suitable engine controller, such as but not limited to a full-authority digital engine or electronic controller (FADEC).

[0064] The ducted-fanless turbine engine 10 includes a set of bleed air ducts 102 that are fluidly coupled to corresponding parts of the ducted-fanless turbine engine 10. As a non-limiting example, the bleed air ducts 102 can be fluidly coupled to the fan section 18, the compressor section 22, or a combination thereof. The set of bleed air ducts 102 is any suitable duct, conduit, tube, passage, etc. for redirecting bleed air from one location to another location. As a non-limiting example, at least one of the bleed air ducts in the set of bleed air ducts 102 can supply bleed air to a downstream or auxiliary part 110 of the turbine engine. The downstream or auxiliary part 110 can be any (multiple) downstream parts of the ducted-fanless turbine engine 10 (e.g., the combustion section 28, the turbine section 32, etc.), (multiple) auxiliary systems (e.g., generators, starters, etc.), or a combination thereof.

[0065] As a non-limiting example, at least one of the group of bleed air ducts 102 may supply bleed air to a corresponding portion of the engine controller 112. As a non-limiting example, the bleed air within at least one of the group of bleed air ducts 102 may be supplied to a sensor 114 to measure at least one of the pressure, velocity, temperature, or a combination thereof of the bleed air provided within the corresponding bleed air duct of the group of bleed air ducts 102. Any number of one or more bleed air ducts of the group of bleed air ducts 102 may be present.

[0066] The ducted fan engine 10 includes a group of discharge assemblies 100. Each discharge assembly of the group of discharge assemblies 100 includes a discharge duct 104. Each discharge assembly of the group of discharge assemblies 100 is coupled at a joint 120 to at least one corresponding bleed air duct of the group of bleed air ducts 102. Each joint 120 is disposed within the fire zone 118 such that at least a portion of each discharge assembly of the group of discharge assemblies 100 is disposed within the fire zone 118. It is contemplated that each discharge assembly of the group of discharge assemblies 100 is coupled to a single bleed air duct or multiple bleed air ducts of the group of bleed air ducts 102. As a non-limiting example, a single discharge assembly of the group of discharge assemblies 100 may be coupled to two or more bleed air ducts of the group of bleed air ducts 102. Any number of one or more discharge assemblies of the group of discharge assemblies 100 may be present.

[0067] The discharge duct 104 extends through a corresponding portion of the fire zone 118 and discharges to the exterior of the fire zone 118. As a non-limiting example, the discharge duct 104 discharges to an area external to the nacelle 40. The discharge assembly 100 is disposed upstream of the location where the engine controller 112 is coupled to the corresponding bleed air duct of the group of bleed air ducts 102 with respect to the fluid flow within the corresponding bleed air duct of the group of bleed air ducts 102.

[0068] The turbofan engine includes a pylon 84. The pylon 84 mounts the ducted fan engine 10 to an external structure (e.g., the fuselage, wing, tail, etc. of an aircraft).

[0069] During operation of the ducted fan engine 10, a free stream airflow 80 flows against the front portion of the ducted fan engine 10. A first portion of the free stream airflow 80 flows along the nacelle 40 and over the group of fan guide vanes 82 as an external airflow 78. The external airflow 78 flows through the group of fan guide vanes 82, follows the curvature of the nacelle 40, and is directed toward the discharge section 38. A second portion of the free stream airflow 80 enters an annular region 25 defined by a swept area between the outer surface of the nacelle 40 and the tips of the fan blades 42, wherein the airflow is a working airflow 76.

[0070] More specifically, working air flow 76 flows into LP compressor 24, and then LP compressor 24 pressurizes working air flow 76, thereby defining a pressurized air flow that is supplied to HP compressor 26, and HP compressor 26 further pressurizes the air. The working air flow 76 or the pressurized air flow from HP compressor 26 is mixed with fuel and ignited in burner 30, thereby generating combustion gases. Some work is extracted from these gases by HP turbine 34, and HP turbine 34 drives HP compressor 26. The combustion gases are discharged into LP turbine 36, and LP turbine 36 extracts additional work to drive LP compressor 24, and the working air flow 76 or the exhaust gases are finally discharged from ducted fan engine 10 via discharge section 38. The driving of LP turbine 36 drives LP shaft 50 to rotate fan 20 and LP compressor 24. The working air flow 76, including the pressurized air flow and the combustion gases, defines the working air flow flowing through compressor section 22, combustion section 28, and turbine section 32 of ducted fan engine 10.

[0071] At least some of external air flow 78 and working air flow 76 converge downstream of discharge section 38 of ducted fan engine 10. Working air flow 76 and external air flow 78 together form the overall thrust of ducted fan engine 10.

[0072] It is contemplated that ducted fan engine 10 sucks working air as bleed air flow from an upstream portion. As a non-limiting example, a first bleed air flow (Fb1) can be sucked from HP compressor 26, a second bleed air flow (Fb2) can be sucked from LP compressor 24, and a third bleed air flow (Fb3) can be sucked from fan section 18. Each bleed air flow is for a specific purpose. As a non-limiting example, the first bleed air flow (Fb1) and the second bleed air flow (Fb2) can be supplied to corresponding portions of engine controller 112 to measure the pressure, velocity, temperature, or a combination thereof of the first bleed air flow (Fb1) and the second bleed air flow (Fb2), respectively. The measurement of the pressure, velocity, and / or temperature of the first bleed air flow (Fb1) and the second bleed air flow (Fb2) can be used to determine the temperature, velocity, and / or pressure of the fluid from the location from which the first bleed air flow (Fb1) or the second bleed air flow (Fb2) is respectively sucked. As a non-limiting example, the third bleed air flow (Fb3) can be supplied to a downstream or auxiliary portion 110 of ducted fan engine 10 to cool the downstream portion of ducted fan engine 10.

[0073] The temperature of the working air flow 76 leaving the burner 30 is significantly elevated relative to the working air flow 76 within the compressor section 22 or the free stream air flow 80 flowing over the set of fan blades 42. As such, the cooling provided by the third bleed air flow (Fb3) is necessary for operating the hot section of the ducted fan engine 10 or such engine components in an environment with elevated temperatures. In the context of a turbine engine, the hot section of the engine is typically downstream of the burner 30, particularly the turbine section 32, where the HP turbine 34 is the hottest part as it is directly downstream of the combustion section 28. Other sources of cooling fluid are fluids bled from the LP compressor 24 or the HP compressor 26, but are not limited thereto.

[0074] It will be appreciated that the illustrated locations from which the first bleed air flow (Fb1), the second bleed air flow (Fb2), and the third bleed air flow (Fb3) are shown as being drawn off are non-limiting examples. The ducted fan engine 10 includes any number of one or more bleed air ducts in the set of bleed air ducts 102, which draw off bleed air from any suitable part of the ducted fan engine 10. As a non-limiting example, compressor bleed air from the compressor section 22 may be drawn off at the outlet of the compressor section 22 or alternatively at the most downstream part of the compressor section 22.

[0075] Although only the first bleed air flow (Fb1), the second bleed air flow (Fb2), and the third bleed air flow (Fb3) are illustrated, it will be appreciated that the ducted fan engine 10 may include any number of one or more bleed air flows. For reference purposes, the first bleed air flow (Fb1), the second bleed air flow (Fb2), the third bleed air flow (Fb3), or any other suitable bleed air flow will hereinafter be referred to as a bleed air flow.

[0076] Since the bleed air flow is drawn off from a fluid (e.g., the free stream air flow 80) that ultimately originates outside the ducted fan engine 10, the bleed air flow may contain moisture. The moisture content of the bleed air flow is based on the humidity of the free stream air flow 80. When the bleed air flow passes through the respective bleed air duct in the set of bleed air ducts 102, the moisture within the bleed air flow may condense within the respective bleed air duct in the set of bleed air ducts 102 and form water droplets. The set of drain assemblies 100 is used to drain the condensate and discharge it as a drain fluid flow (Fd) outside the fire zone 118.

[0077] The connector 120 is disposed upstream of the FFLZ 164; specifically, upstream of the engine controller 112 and the sensor 114. Positioning the connector 120 upstream of the FFLZ ensures that condensate within the respective bleed air ducts of the set of bleed air ducts 102 is discharged from the system before the bleed air stream is supplied to the engine controller 112. It is contemplated that direct contact between the condensate and the electronics of the engine controller 112 could cause failure of some portions of the engine controller 112.

[0078] Positioning the connector 120 within the fire zone 118 ensures that the moisture within the bleed air stream is at a temperature sufficient to form condensate. Additionally, positioning the connector 120 within the fire zone 118 ensures that the condensate does not freeze within the set of discharge assemblies 100.

[0079] Positioning the connection portion of the engine controller 112 (e.g., the position where the sensor 114 is positioned within or along the set of bleed air ducts 102) as close as possible to the connector 120 and downstream of the connector 120 reduces the pressure drop associated with the bleed air stream within the set of bleed air ducts 102. The reduction in pressure drop in turn ensures that the measured pressure, velocity, temperature, or combination thereof of the bleed air stream is closer to the pressure, velocity, temperature, or combination thereof of the working air stream from which the bleed air stream is drawn. Positioning the connection portion of the engine controller 112 as close as possible to the connector 120 further reduces the footprint of the set of bleed air ducts 102, and thus reduces the space required within the ducted fan engine 10 for the set of bleed air ducts 102.

[0080] When the bleed air stream within the set of bleed air ducts 102 is supplied to the respective sensors 114, the bleed air stream within the bleed air ducts 102 may be discharged to the atmosphere or redirected back into the ducted fan engine 10 after passing through or by the sensors 114. As discussed herein, the purpose of the sensors 114 is to measure the temperature, velocity, pressure, or combination thereof of the bleed air within the respective bleed air ducts. If the sole purpose of the bleed air ducts 102 is to supply the bleed air stream to the sensors 114, the bleed air ducts 102 are defined as sensing ducts.

[0081] Figure 2 is a schematic illustration of a discharge assembly 200 that is fluidly coupled to a bleed air duct 202 suitable for use within a Figure 1 ducted fan engine 10. The discharge assembly 200 and the bleed air duct 202 are respectively similar to the discharge assembly 100 ( Figure 1 ) and the bleed air duct 102 ( Figure 1);Therefore, similar components will be identified using similar numbers added to the 200 series, with the understanding that the descriptions of the exhaust assembly 100 and the bleed air duct 102 apply to the exhaust assembly 200 and the bleed air duct 202 respectively, unless otherwise indicated.

[0082] The bleed air duct 202 and the exhaust assembly 200 are disposed within a turbomachine (e.g., Figure 1 a ducted turbofan 10). The turbomachine includes a combustion zone 218 and a FFLZ 264. At least a portion of the bleed air duct 202 and the exhaust assembly 200 are disposed within the combustion zone 218. The bleed air duct 202 supplies into the FFLZ 264. The exhaust assembly 200 is disposed along a corresponding portion of the bleed air duct 202. The exhaust assembly 200 includes an exhaust duct 204 that leads to a region external to the combustion zone 218 at an exhaust outlet (not shown).

[0083] The bleed air duct 202 fluidly couples a bleed air flow (Fb) from an upstream section of the turbomachine to a downstream or accessory portion of the turbomachine. The bleed air flow (Fb) can be any suitable bleed air flow, such as but not limited to Figure 1 a first bleed air flow (Fb1), Figure 1 a second bleed air flow (Fb2), Figure 1 a third bleed air flow (Fb3) or any other suitable bleed air flow. An exhaust fluid flow (Fd) flows through the exhaust assembly 200 and ultimately to a region external to the combustion zone 218.

[0084] The exhaust assembly 200 is fluidly coupled to a corresponding portion of the bleed air duct 202 at a joint 220. The joint 220 is within the combustion zone 218. The joint 220 is upstream of the FFLZ 264. The joint 220 is defined as a three-dimensional region where a passage leading to the exhaust duct 204 intersects the bleed air duct 202. The exhaust assembly 200 includes a joint fitting 222, a bleed hole fitting 232, and the exhaust duct 204.

[0085] The joint fitting 222 includes a joint 220. The joint fitting 222 is any suitable fitting, including but not limited to a T-joint fitting, a Y-joint fitting, etc. As a non-limiting example, the joint fitting 222 is a T-joint fitting, which includes a stem portion 226 and a top portion 224 that extends transversely to the stem portion 226. The top portion 224 includes a first internal passage 252. The stem portion includes a second internal passage 254. The joint 220 is defined as the region where the second internal passage 254 is fluidly coupled to and intersects the first internal passage 252. The first internal passage 252 is defined as a continuation of the bleed air duct 202. Thus, at least a portion of the bleed assembly 200 defines a corresponding portion of the bleed air duct 202. The second internal passage 254 may be defined as a continuation of a passage that ultimately leads to the discharge duct 204 or alternatively may be defined as the starting point of a passage that ultimately leads to the discharge duct 204. The second internal passage 254 is defined by a maximum diameter (D).

[0086] The bleed assembly 200 is coupled to the bleed air duct 202 via the joint fitting 222 or is integrally formed with the bleed air duct 202. When coupled to the bleed air duct 202, a transition portion 230 is formed between the body of the joint fitting 222 and the body of the bleed air duct 202. The bleed assembly 200 may be retrofitted to a bleed air duct 202 that has already been manufactured or already connected (e.g., installed) within a corresponding turbine engine. Thus, the bleed assembly 200 may be defined as a retrofit bleed assembly. The bleed air duct 202 may be coupled to the bleed assembly 200 via the joint fitting 222 at the transition portion 230 by any suitable coupling method such as but not limited to welding, gluing, bonding, fastening, etc. Alternatively, the joint fitting 222 may be integrally formed with the bleed air duct 202.

[0087] The bleed hole fitting 232 includes a bleed hole 240. The bleed hole 240 includes a bleed hole diameter (Dw). The bleed hole diameter (Dw) is the minimum diameter of the fluid passage within the bleed hole fitting 232. Thus, the bleed hole 240 defines a portion of the bleed assembly 200 having a reduced diameter.

[0088] The bleed hole 240 may define an inlet to the discharge duct 204. The bleed hole fitting 232 may include a funnel portion 242 that defines an inlet to the bleed hole 240. The bleed hole fitting 232 may include a flare portion 244. The flare portion 244 defines a portion of the bleed hole 240 that has a cross-sectional area that increases from the bleed hole diameter (Dw). The flare portion 244 serves to prevent surface tension along the bleed hole 240 and thus prevent a large amount of water from remaining along the surface of the bleed hole 240.

[0089] The positioning of the bleed hole 240 relative to the fitting 220 is defined by a length (L). The length (L) is the minimum straight-line distance between the starting point of the bleed hole 240 (e.g., the location where the funnel portion 242 intersects the bleed hole 240) and the nearest point on the fitting 220 to the starting point of the bleed hole 240. The ratio between the length (L) and the maximum diameter (D) is used to define the volume of the region between the fitting 220 and the bleed hole 240. As a non-limiting example, the ratio of the length (L) to the diameter (D) (e.g., the L / D ratio) is greater than or equal to 4 and less than or equal to 8.

[0090] The discharge assembly 200 may include a connection fitting 236 extending between the bleed hole fitting 232 and the discharge conduit 204. The connection fitting 236 is formed separately from the bleed hole fitting 232 and the discharge conduit 204. The connection fitting 236 can be any suitable fitting, such as but not limited to a nipple fitting. The connection fitting 236 can be coupled to the bleed hole fitting 232 and the discharge conduit 204 by any suitable method, such as but not limited to welding, bonding, fastening, threading, or a combination thereof. As a non-limiting example, the connection fitting 236 can be fastened to the bleed hole fitting 232 and the discharge conduit 204 using a connector 234. The connector 234 is at least partially surrounded by the connection fitting 236 and is coupled to (e.g., by welding, bonding, fastening, threading, etc.) the corresponding portions of the bleed hole fitting 232 and the discharge conduit 204.

[0091] Although illustrated as including the connection fitting 236 and the connector 234, it will be appreciated that the connection fitting 236, the connector 234, or both the connection fitting 236 and the connector 234 can be excluded from the discharge assembly 200. Thus, the bleed hole fitting 232 can be directly coupled to (e.g., in contact with) the discharge conduit 204 or otherwise integrally formed with the discharge conduit 204.

[0092] The bleed hole fitting 232 is coupled to the fitting fitting 222 by any suitable coupling method, such as but not limited to welding, bonding, fastening, threading, or a combination thereof. Alternatively, the bleed hole fitting 232 can be integrally formed with the fitting fitting 222.

[0093] During operation, the bleed air flow (Fb) is supplied through the bleed air conduit 202 and through the first internal passage 252 of the fitting fitting 222. The condensate flow (Fco) flows through the second internal passage 254 and collects in the region between the fitting 220 and the bleed hole 240. The condensate flow (Fco) flows through the bleed hole 240 and into the discharge conduit 204 as the discharge fluid flow (Fd).

[0094] The discharge assembly 200 is oriented such that the condensate stream (Fco) flows by gravity, illustrated by arrow (Fg), into the region between the fitting 220 and the bleed hole 240. The reduced cross-sectional area of the bleed hole 240 prevents the bleed air stream (Fb) from flowing into the second internal passage 254 and into the bleed hole 240.

[0095] The volume of the condensate stream (Fco) and thus the amount of condensate that accumulates in the region between the fitting 220 and the bleed hole 240 varies based on the operation of the turbine engine. As a non-limiting example, a turbine engine operating in a humid climate will have a more humid bleed air stream (Fb) and thus a greater volume of condensate from the condensate stream (Fco) compared to a turbine engine operating in an arid or less humid environment.

[0096] The length (L) and the maximum diameter (D) are selected based on the expected maximum condensate volume from the condensate stream (Fco). As a non-limiting example, if a larger condensate volume is expected, a larger length (L), a larger maximum diameter (D), or a combination thereof may be selected. In other words, the length (L) and the maximum diameter (D) are selected to form sufficient space for the condensate to accumulate and to ensure that the condensate does not overflow past the fitting 220 and into the downstream portion of the bleed air duct 202.

[0097] Figure 3 is Figure 2 A schematic representation of the bleed air duct 202. The discharge assembly 200 may be included within a group of discharge assemblies 200 disposed along the bleed air duct 202. Each discharge assembly within the group of discharge assemblies 200 is disposed within the fire zone 218 and upstream of the FFLZ 264, or alternatively at a location where the engine controller 212 is coupled to the bleed air duct 202. As a non-limiting example, the engine controller 212 may be coupled to the bleed air duct 202 via a sensor 214.

[0098] The group of discharge assemblies 200 may include any number of one or more discharge assemblies 200. As a non-limiting example, the group of discharge assemblies 200 may include a first discharge assembly 200a, a second discharge assembly 200b, and a third discharge assembly 200c disposed along a single bleed air duct 202. The first discharge assembly 200a may be coupled to the bleed air duct 202 at a first fitting 246. The second discharge assembly 200b may be coupled to the bleed air duct 202 at a second fitting 248. The third discharge assembly 200c may be coupled to the bleed air duct 202 at a third fitting 250.

[0099] Two or more of the grouped bleed assemblies 200 can include a common (e.g., single) bleed duct 204. As a non-limiting example, a second bleed assembly 200b and a third bleed assembly 200c can extend from a second fitting 248 and a third fitting 250, respectively, and extend to a single common bleed duct 204. It will be appreciated that the second fitting 248 and the third fitting 250 can be positioned along the same bleed air duct 202, as illustrated. Alternatively, the second fitting 248 can be disposed along the bleed air duct 202, while the second fitting 250 can be disposed along another bleed air duct separate from the bleed air duct 202.

[0100] The bleed air duct 202 includes a grouped valley portion 258. Each of the first fitting 246, the second fitting 248, the third fitting 250, or any other fitting 220 is disposed within the gravity low point of a corresponding valley portion of the grouped valley portion 258. As used herein, "gravity low point" refers to the portion of a corresponding valley portion of the grouped valley portion 258 that is the minimum or lowest point relative to gravity (Fg). Positioning the first fitting 246, the second fitting 248, the third fitting 250, or any other fitting 220 ( Figure 2 ) at the gravity low point ensures that condensate from the bleed air flow (Fb) ( Figure 2 ) will flow into the corresponding bleed duct 204. Each valley portion of the grouped valley portion 258 includes a single fitting 220. Alternatively, two or more fittings 220 can be disposed within a single valley portion of the grouped valley portion 258.

[0101] Figure 4 is a schematic illustration of an exemplary bleed assembly 300 that is fluidly coupled to a bleed air duct 302 adapted for use within a ducted fanless turbine engine 10. The bleed assembly 300 and the bleed air duct 302 are respectively similar to the bleed assembly 100 ( Figure 1 ), 200 ( Figure 1 ), and the bleed air duct 102 ( Figure 2 ), 202 ( Figure 1 ); thus, like components will be identified with like numbers incremented to the 300 series, with the understanding that the descriptions of the bleed assemblies 100, 200 and the bleed air ducts 102, 202 apply to the bleed assembly 300 and the bleed air duct 302, respectively, unless otherwise noted. Figure 2 ) and 202 (

[0102] At least a portion of each of the bleed air duct 302 and the bleed assembly 300 is disposed within the turbine engine (e.g., Figure 1within the fire zone 318 of the ducted fanless turbine engine 10). The turbine engine further includes the FFLZ 364. The discharge assembly 300 is disposed along a corresponding portion of the bleed air duct 302. The discharge assembly 300 is fluidly coupled to the corresponding portion of the bleed air duct 302 at the fitting 320. The discharge assembly 300 includes a fitting assembly 322, which includes the fitting 320, a first internal passage 352, and a second internal passage 354. The fitting assembly 322 is coupled to the bleed air duct 302 at the transition 330 or is integrally formed with the bleed air duct 302. The fitting assembly 322 can be any suitable fitting, such as but not limited to a T-shaped fitting having a stem 326 and a top 324. The discharge assembly 300 includes a discharge duct 304 that leads to an area external to the fire zone 318 at a discharge outlet (not shown). The discharge assembly includes a connection fitting 336 and a connector 334 that secures at least the connection fitting 336 to the discharge duct 304. The fitting assembly 322 is disposed along a portion of the discharge assembly 300 that ensures that condensate from the bleed air flow (e.g., Figure 2 ) of the bleed air flow (Fb) will flow by gravity, as designated by the arrow (Fg), into the discharge duct 304. The fitting 320 is disposed within the fire zone 318. The fitting 320 is upstream of the FFLZ 364.

[0103] The discharge assembly 300 is similar to the discharge assembly 200 in that the discharge assembly 300 includes a weep hole 340 that fluidly couples the second internal passage 354 to a corresponding portion of the discharge assembly 300 (e.g., the connection fitting 336). The weep hole 340 is disposed within the fire zone 318. The discharge assembly 300 includes a funnel portion 342 that defines an inlet to the weep hole 340, and a diffuser portion 344. Different from the weep hole 240 ( Figure 2 ), the weep hole 340 is formed within the fitting assembly 322. In other words, the fitting assembly 322 is a fitting that includes the first internal passage 352, the second internal passage 354, the fitting 320, the funnel portion 342, the weep hole 340, and the diffuser portion 344. Using the fitting assembly 322 that includes the weep hole 340 eliminates the need for a physical connection between the weep hole fitting (e.g., Figure 2 ) of the weep hole fitting 232) and the fitting assembly 322, thus reducing the complexity of the discharge assembly 300.

[0104] The fitting assembly 322 is directly coupled to the connection fitting 336 via the connector 334. Although shown as including the connection fitting 336 and the connector 334, it will be appreciated that the connection fitting 336, the connector 334, or both the connection fitting 336 and the connector 334 can be excluded from the discharge assembly 300 such that the fitting assembly 322 is directly coupled to (e.g., in contact with) the discharge duct 304.

[0105] Figure 5 is fluidly coupled to a suitable one for use inFigure 1 Schematic illustration of an exemplary drain assembly 400 for a bleed air duct 402 used within a ducted fanless turbomachine 10. Drain assembly 400 and bleed air duct 402 are respectively similar to drain assemblies 100( Figure 1 ), 200( Figure 2 ), 300( Figure 4 ) and bleed air ducts 102( Figure 1 ), 202( Figure 2 ), 302( Figure 4 ); thus, like components will be identified with like numbers incremented to the 400 series, with the understanding that the descriptions of drain assemblies 100, 200, 300 and bleed air ducts 102, 202, 302 apply respectively to drain assembly 400 and bleed air duct 402 unless otherwise indicated.

[0106] At least a portion of each of bleed air duct 402 and drain assembly 400 is disposed within the fire zone 418 of a turbomachine (e.g., Figure 1 ducted fanless turbomachine 10). The turbomachine includes a FFLZ 464. Drain assembly 400 is disposed along a corresponding portion of bleed air duct 402. Drain assembly 400 is fluidly coupled to the corresponding portion of bleed air duct 402 at a junction 420. Drain assembly 400 includes a fitting 422 which includes junction 420, a first internal passage 452 and a second internal passage 454. Fitting 422 is coupled to or integrally formed with bleed air duct 402 at a transition 430. Fitting 422 can be any suitable fitting, such as but not limited to a T-shaped fitting having a stem 426 and a top 424. Drain assembly 400 includes a drain duct 404 which leads to a region external to fire zone 418 at a drain outlet. Fitting 422 is disposed along a portion of drain assembly 400 which ensures that condensate from the bleed air flow (e.g., Figure 2 bleed air flow (Fb)) will flow by gravity, as designated by arrow (Fg), into drain duct 404. Junction 420 is disposed within fire zone 418. Junction 420 is upstream of FFLZ 464.

[0107] Drain assembly 400 is similar to drain assembly 200 in that drain assembly 400 includes a weep hole fitting 432 having weep holes 440. Weep hole fitting 432 is disposed within fire zone 418. Similar to weep hole fitting 232( Figure 2) The same, the bleed hole fitting 432 includes a funnel portion 442 and a dilation portion 444, and is coupled to the adapter fitting 422 through a connection fitting 434. However, the bleed hole fitting 432 is directly coupled to (e.g., in contact with) the discharge pipe 404 by any suitable method (such as but not limited to welding, bonding, fastening, threading, etc.). As a non-limiting example, the bleed hole fitting 432 is a type B nut that is threadedly coupled to the discharge pipe 404. The use of the discharge assembly 400 eliminates the need for a connector (e.g., connector 234( Figure 2 ), 334( Figure 4 )); thus, reducing the complexity of the discharge assembly 400 and the burden of manufacturing the discharge assembly 400.

[0108] Figure 6 is fluidly coupled to an exemplary discharge assembly 500 of a bleed air duct 502 suitable for use within a ducted fan engine 10 Figure 1 . A schematic illustration of the discharge assembly 500. The discharge assembly 500 and the bleed air duct 502 are respectively similar to the discharge assemblies 100( Figure 1 ), 200( Figure 2 ), 300( Figure 4 ), 400( Figure 5 ) and the bleed air ducts 102( Figure 1 ), 202( Figure 2 ), 302( Figure 5 ), 402( Figure 5 ); thus, similar components will be identified with similar numbers incremented to the 500 series, with the understanding that the descriptions of the discharge assemblies 100, 200, 300, 400 and the bleed air ducts 102, 202, 302, 402 apply respectively to the discharge assembly 500 and the bleed air duct 502, unless otherwise indicated.

[0109] At least a portion of each of the bleed air duct 502 and the discharge assembly 500 is disposed within the fire zone 518 of a turbofan engine (e.g., Figure 1 's ducted fan engine 10). The turbofan engine includes an FFLZ 564. The discharge assembly 500 is disposed along a corresponding portion of the bleed air duct 502. The discharge assembly 500 is fluidly coupled to the corresponding portion of the bleed air duct 502 at a joint 520. The discharge assembly 500 includes an adapter fitting 522, which includes a joint 520, a first internal passage 552 and a second internal passage 554. The adapter fitting 522 is coupled to or integrally formed with the bleed air duct 502 at a transition portion 530. The adapter fitting 522 can be any suitable fitting, such as but not limited to a T-shaped fitting having a stem portion 526 and a top portion 524. The joint 520 is disposed within the fire zone 518. The joint 520 is upstream of the FFLZ 564.

[0110] Similar to the bleed assemblies 200, 400, the bleed assembly 500 includes a bleed orifice fitting 532, which includes a bleed orifice 540, a funnel portion 542, and a dilation portion 544. However, the bleed orifice fitting 532 is at least partially disposed in a region outside the fire zone 518. As a non-limiting example, the bleed orifice fitting 532 is entirely disposed within a region outside the fire zone 518. The bleed orifice fitting 532 includes a discharge outlet 506 that leads directly to a region outside the fire zone 518. A joint fitting 522 is disposed along a portion of the bleed assembly 500 that ensures that condensate from the bleed air stream (e.g., Figure 2 the bleed air stream (Fb)) will flow by gravity, as designated by the arrow (Fg), into the discharge duct 504.

[0111] The bleed orifice fitting 532 is coupled to the discharge duct 504 by any suitable means (such as but not limited to welding, gluing, fastening, threading, etc.). The discharge duct 504 is coupled to the joint fitting 522 by any suitable means (such as but not limited to welding, gluing, fastening, threading, etc.).

[0112] The bleed assembly 500 includes a larger region between the bleed orifice 540 and the joint 520. Thus, the bleed assembly 500 includes a larger region relative to the bleed assemblies 200, 300, 400 to hold condensate. It is contemplated that the bleed assembly 500 can be used in a turbomachine expected to be used in a high humidity region or otherwise in a region expected to have a large volume of condensate.

[0113] Figure 7 is a schematic illustration of an exemplary bleed assembly 600 that is fluidly coupled to a bleed air duct 402 suitable for use within a Figure 1 ducted turbomachine 10. The bleed assembly 600 and the bleed air duct 602 are respectively similar to the bleed assemblies 100 ( Figure 1 ), 200 ( Figure 2 ), ३०० ( Figure 4 ), 400 ( Figure 5 ), 500 ( Figure 6 ) and the bleed air ducts 102 ( Figure 1 ), 202 ( Figure 2 ), 302 ( Figure 4 ), 402 ( Figure 5 ), 502 ( Figure 6 ); thus, like components will be denoted with like numerals incremented to the 600 series, with the understanding that the descriptions of the bleed assemblies 100, 200, 300, 400, 500 and the bleed air ducts 102, 202, 302, 402, 502 apply to the bleed assembly 600 and the bleed air duct 602 respectively, unless otherwise indicated.

[0114] At least a portion of each of the bleed air duct 602 and the discharge assembly 600 is disposed within the fire zone 618 of a turbomachine (e.g., Figure 1 the ducted fan turbomachine 10). The turbomachine includes an FFLZ 664. The discharge assembly 600 is disposed along a corresponding portion of the bleed air duct 602. The discharge assembly 600 is fluidly coupled to the corresponding portion of the bleed air duct 602 at a joint 620. The discharge assembly 600 includes a joint fitting 622 that includes the joint 620, a first internal passage 652, and a second internal passage 654. The joint fitting 622 is coupled to or integrally formed with the bleed air duct 602 at a transition 630. The joint fitting 622 can be any suitable fitting, such as but not limited to a T-fitting having a stem 626 and a top 624. The discharge assembly 600 includes a discharge duct 604 that leads to an area external to the fire zone 618 at a discharge outlet (not shown). The joint fitting 622 is disposed along a portion of the discharge assembly 600 that ensures that condensate from the bleed air flow (e.g., Figure 2 the bleed air flow (Fb)) will flow by gravity, as designated by arrow (Fg), into the discharge duct 604. The joint 620 is disposed within the fire zone 618. The joint 620 is upstream of the FFLZ 664.

[0115] Similar to the discharge assemblies 100, 200, 300, 400, 500, the discharge assembly 600 includes a weep hole 640, a funnel portion 642, and a flare portion 644. However, the weep hole 640 includes a first portion 640a formed within or otherwise by the joint fitting 622 (e.g., similar to Figure 4 the weep hole 340) and a second portion 640b formed within or otherwise by the discharge duct 604. As a non-limiting example, the flare portion 644 and at least the second portion of the weep hole 640 are formed by the discharge duct 604, while the funnel portion 642 and the first portion of the weep hole 640 are formed by the joint fitting 622. Alternatively, all of the weep hole 640 can be formed by one of the joint fitting 622 or the discharge duct 604. The dissection of the weep hole 640 between the joint fitting 622 and the discharge duct 604 allows for design variations within the weep hole 640. For example, if a larger flare portion 644 is desired at a later time, only the discharge duct 604 needs to be replaced, rather than the entire weep hole 640.

[0116] In the case of the configuration of the discharge assembly 600, the discharge duct 604 is in direct contact with the joint fitting 622. A connection fitting 636 couples the discharge duct 604 to the joint fitting 622. The connection fitting 636 can be any suitable connector. Alternatively, the discharge duct 604 can be coupled to the joint fitting 622 by a joining method such as but not limited to welding or bonding.

[0117] Figure 8 is a schematic illustration of an exemplary discharge assembly 700 of a fluid coupled to a bleed air duct 402 adapted for use within a ducted fanless turbine engine 10 of Figure 1 . The discharge assembly 700 and the bleed air duct 702 are respectively similar to the discharge assemblies 100 ( Figure 1 ), 200 ( Figure 2 ), 300 ( Figure 4 ), 400 ( Figure 5 ), 500 ( Figure 6 ), 600 ( Figure 7 ) and the bleed air ducts 102 ( Figure 1 ), 202 ( Figure 2 ), 302 ( Figure 4 ), 402 ( Figure 5 ), 502 ( Figure 6 ), 602 ( Figure 7 ); accordingly, like parts will be identified with like numerals incremented to the 700 series, with the understanding that the descriptions of the discharge assemblies 100, 200, 300, 400, 500, 600 and the bleed air ducts 102, 202, 302, 402, 502, 602 respectively apply to the discharge assembly 700 and the bleed air duct 702, unless otherwise indicated.

[0118] At least portions of each of the bleed air duct 702 and the discharge assembly 700 are disposed within a fire zone 718 of a turbine engine (e.g., Figure 1 's ducted fanless turbine engine 10). The turbine engine includes an FFLZ 764. The discharge assembly 700 is disposed along a corresponding portion of the bleed air duct 702. The discharge assembly 700 is fluidly coupled to the corresponding portion of the bleed air duct 702 at a joint 720. The discharge assembly 700 includes a joint fitting 722, which includes a joint 720, a first internal passage 752 and a second internal passage 754. The joint fitting 722 is coupled to or integrally formed with the bleed air duct 702 at a transition 730. The joint fitting 722 can be any suitable fitting, such as but not limited to a T-fitting having a stem 726 and a top 724. The discharge assembly 700 includes a discharge duct 704, which leads to an area external to the fire zone 718 at a discharge outlet (not shown). The joint fitting 722 is disposed along a portion of the discharge assembly 700 that ensures that condensate from the bleed air flow (e.g., Figure 2 's bleed air flow (Fb)) will flow by gravity, as designated by an arrow (Fg), into the discharge duct 704. The joint 720 is disposed within the fire zone 718. The joint 720 is upstream of the FFLZ 764.

[0119] Similar to the discharge assembly 200, the discharge assembly 700 includes a bleed hole 740, a funnel portion 742, and a dilation portion 744 formed within the fitting 722. The fitting 722 is coupled to the discharge conduit 704 by using a lip 756 and a seat 758. The lip 756 is a protrusion sized to abut or otherwise be received within the seat 758. The lip 756 and the seat 758 may be provided along any suitable portion of the discharge assembly 700. As a non-limiting example, the lip 756 may be provided along the discharge conduit 704, while the seat 758 may be provided along the fitting 722. During assembly, the discharge conduit 704 may be compressed inwardly (e.g., by compression from a hand or tool) and inserted into the fitting 722. Once the force is removed, the discharge conduit 704 expands and the lip 756 is received within the seat 758.

[0120] Although described in terms of the fitting 722 including the seat 758, additional components are contemplated. As a non-limiting example, a connecting fitting (e.g., connecting fitting 234( Figure 1 ), 334( Figure 4 )) including the seat 758 or the lip 756 may be threadably coupled to or otherwise coupled to the fitting 722. As a non-limiting example, a bleed hole fitting (e.g., bleed hole fitting 232( Figure 2 ), 432( Figure 5 )) including the seat 758 or the lip 756 may be threadably coupled to or otherwise coupled to the fitting 722. Then, the discharge conduit 704 including the other of the lip 756 or the seat 758 may be coupled to the connecting fitting or the bleed hole fitting, thereby effectively coupling the discharge conduit 704 to the fitting 722. The reverse configuration is contemplated, where the connector is threadably coupled to the discharge conduit 704 and the fitting includes one of the lip 756 or the seat 758.

[0121] Using the lip 756 and the seat 758 allows for a reduced manufacturing burden. In addition, the coupling formed by the lip 756 and the seat 758 is reversible. In other words, when the lip 756 is disposed within the seat 758, the discharge conduit 704 may be compressed again and removed from the fitting 722.

[0122] Figure 9 is a schematic illustration of an exemplary discharge assembly 800 that is fluidly coupled to a bleed air conduit 802 adapted for use within a ducted fan engine 10. The discharge assembly 800 and the bleed air conduit 802 are respectively similar to the discharge assemblies 100( Figure 1 ), 200( Figure 1 ), 300( Figure 2 ), 400( Figure 4 ), 500( Figure )、500(​ )、600( ​ )、700( ​ ) and extraction air duct 102( ​ )、202( ​ )、302( ​ )、402( ​ )、502( ​ )、602( ​ )、702( ​ );Therefore, similar components will be identified by similar numbers incremented to the 800 series, with the understanding that the descriptions of the bleed assemblies 100, 200, 300, 400, 500, 600, 700 and the extraction air ducts 102, 202, 302, 402, 502, 602, 702 apply respectively to the bleed assembly 800 and the extraction air duct 802, unless otherwise indicated.

[0123] At least a portion of each of the extraction air duct 802 and the bleed assembly 800 is disposed within the fire zone 818 of a turbomachine (e.g., ​ the ducted turbofan 10). The turbomachine includes an FFLZ 864. The bleed assembly 800 is disposed along a corresponding portion of the extraction air duct 802. The bleed assembly 800 is fluidly coupled to the corresponding portion of the extraction air duct 802 at a joint 820. The bleed assembly 800 includes a joint fitting 822, which includes a joint 820, a first internal passage 852, and a second internal passage 854. The joint fitting 822 is coupled to or integrally formed with the extraction air duct 802 at a transition 830. The joint fitting 822 can be any suitable fitting, such as but not limited to a T-shaped fitting having a stem 826 and a top 824. The bleed assembly 800 includes a bleed duct 804, which leads to an area external to the fire zone 818 at a bleed outlet (not shown). The joint fitting 822 is disposed along a portion of the bleed assembly 800 that ensures that condensate from the extraction air flow (e.g., ​ the extraction air flow (Fb)) will flow by gravity, as indicated by the arrow (Fg), into the bleed duct 804. The joint 820 is disposed within the fire zone 818. The joint 820 is upstream of the FFLZ 864.

[0124] Similar to the discharge assemblies 200, 400, the discharge assembly 800 includes a bleed hole fitting 832 having a bleed hole 840, a funnel portion 842, and a flare portion 844. However, the bleed hole fitting 832 is partially surrounded by a fitting adapter 822 and a receiving portion of the discharge conduit 804. As a non-limiting example, the fitting adapter 822 includes a first protrusion 860 and the discharge conduit 804 includes a second protrusion 862. The first protrusion 860 surrounds (e.g., encircles) a first portion of the bleed hole fitting 832. The second protrusion 862 surrounds (e.g., encircles) a second portion of the bleed hole fitting 832.

[0125] The first protrusion 860 and the second protrusion 862 may each include a series of threads (not shown). The bleed hole fitting 832 may include a series of threads (not shown) that mate with a series of threads provided on the first protrusion 860 and the second protrusion 862. The bleed hole fitting 832 may be threadably coupled to the fitting adapter 822 and the discharge conduit 804 using the first protrusion 860 and the second protrusion 862. When the bleed hole fitting 832 is threadably coupled to the fitting adapter 822 and the discharge conduit 804, the bleed hole fitting 832 is removably coupled to the fitting adapter 822 and the discharge conduit 804.

[0126] Using a bleed hole fitting 832 that is removably coupled to at least one of the fitting adapter 822, the discharge conduit 804, or a combination thereof allows for a reduction in the manufacturing and maintenance burden of the discharge assembly 800. For example, it is envisioned that using threads to secure the bleed hole fitting 832 to the corresponding portions of the discharge assembly 800 is easier than welding, gluing, or fastening the bleed hole fitting 832 to the corresponding portions of the discharge assembly 800; thus, reducing the manufacturing burden. Additionally, it is envisioned that threads are easier to disengage than welds, adhesives, or fasteners. Accordingly, components of the discharge assembly 800 (e.g., the bleed hole fitting 832) can be easily disengaged during maintenance of the discharge assembly 800 to be inspected, cleaned, or replaced.

[0127] ​ is fluidly coupled to an exemplary discharge assembly 900 of a bleed air conduit 402 adapted for use within a ​ ducted fan engine 10. The discharge assembly 900 and the bleed air conduit 902 are respectively similar to the discharge assemblies 100 ( ​ ), 200 ( ​ ), 300 ( ​ ), 400 ( ​ ), 500 ( ​ ), 600 ( ​ ), 700 ( ​ ), 800 ( ​ ) and the bleed air conduits 102 ( ​ ), 202 ( ​)、302( ​ )、402( ​ )、502( ​ )、602( ​ )、702( ​ )、802( ​ );Therefore, similar components will be identified with similar numbers incremented to the 900 series, with the understanding that the descriptions of the bleed assemblies 100, 200, 300, 400, 500, 600, 700, 800 and the bleed air ducts 102, 202, 302, 402, 502, 602, 702, 802 apply to the bleed assembly 900 and the bleed air duct 902 respectively, unless otherwise indicated.

[0128] At least a portion of each of the bleed air duct 902 and the bleed assembly 900 is disposed within the fire zone 918 of a turbomachine (e.g., ​ the ducted fan turbomachine 10). The turbomachine includes an FFLZ 964. The bleed assembly 900 is disposed along a corresponding portion of the bleed air duct 902. The bleed assembly 900 is fluidly coupled to the corresponding portion of the bleed air duct 902 at a joint 920. The bleed assembly 900 includes a joint fitting 922 that includes the joint 920, a first internal passage 952, and a second internal passage 954. The joint fitting 922 is coupled to or integrally formed with the bleed air duct 902 at a transition 930. The bleed assembly 900 includes a bleed duct 904 that leads to a region external to the fire zone 918 at a bleed outlet (not shown). The joint fitting 922 is disposed along a portion of the bleed assembly 900 that ensures that condensate of the bleed air flow (e.g., ​ the bleed air flow (Fb)) will flow by gravity, as designated by an arrow (Fg), into the bleed duct 904. The bleed assembly 900 may include a connector 934 that couples a weep hole fitting 932 to the bleed duct 904. The connector 934 and the weep hole fitting 932 may be coupled via a connection fitting 936. The joint 920 is disposed within the fire zone 918. The joint 920 is upstream of the FFLZ 964.

[0129] Similar to the bleed assemblies 200, 400, 800, the bleed assembly 900 includes a weep hole fitting 932 that has a weep hole 940, a funnel portion 942, and a flare portion 944. As illustrated, the bleed assembly 900 is defined by a Y-joint having a stem portion 926 and a top portion 924. The top portion 924 is defined by the joint fitting 922. The stem portion 926 may be defined by the weep hole fitting 932 and the bleed duct 904. The joint 920 is disposed at the lowest gravity portion of the top portion 924.

[0130] In some instances, using a Y-joint can reduce the footprint of the discharge assembly 900. Additionally, using a Y-joint directs the bleed air flow within the bleed air duct 902 directly toward the discharge assembly 900, thus increasing the likelihood that condensate within the bleed air flow enters the discharge assembly 900.

[0131] Reference ​ , it will be appreciated that the fitting assemblies 222, 322, 422, 522, 622, 722, 822, 922 are any suitable fitting assemblies to which the discharge ducts 204, 304, 404, 504, 604, 704, 804, 904 can be coupled to the lowest gravity portion of the fitting assemblies 222, 322, 422, 522, 622, 722, 822, 922. By way of non-limiting example, the fitting assemblies 222, 322, 422, 522, 622, 722, 822, 922 are T-joints ( ​ ), Y-joints ( ​ ), etc. The discharge ducts 204, 304, 404, 504, 604, 704, 804, 904 are further coupled to the bleed air ducts 202, 302, 402, 502, 602, 702, 802, 902 or otherwise coupled to the fitting assemblies 222, 322, 422, 522, 622, 722, 822, 922 by any suitable means such as but not limited to welding, gluing, threading, bonding, friction contact, snap fittings, etc.

[0132] Benefits include a turbine engine that is more aerodynamically efficient when compared to a conventional turbine engine. For example, a conventional turbine engine includes a fan case that houses the engine controller(s) or otherwise provides a point for coupling the engine controller(s). The engine controller(s) are positioned along the fan case such that the engine controller(s) are positioned in an area of the turbine engine outside of the fire zone. Positioning the engine controller(s) outside of the fire zone is done to avoid exposing the engine controller(s) to temperatures that exceed the acceptable temperature of the engine controller (e.g., the temperature at which the engine controller(s) can function) generated by the turbine engine. However, the architecture required to mount the engine controller to the fan case requires space, which affects the aerodynamic profile of the fan case. However, a turbine engine as described herein mounts the engine controller(s) to the engine case rather than the fan case, or to another external portion of the turbine engine (e.g., the nacelle or cowling). As such, no additional architecture that would negatively impact the aerodynamic profile of the turbine engine is required, thus resulting in a turbine engine that has a higher aerodynamic efficiency when compared to a conventional turbine engine.

[0133] However, when it comes to discharging condensate from the (multiple) bleed air ducts, positioning the (multiple) engine controllers along the engine casing can pose a problem. In a conventional turbofan engine, the (multiple) bleed air ducts are routed to an area outside the fire zone and there is sufficient space between the fire zone and the (multiple) engine controllers to provide the architecture required for discharging condensate from the (multiple) bleed air ducts. The (multiple) bleed air ducts as described herein do not have sufficient space between the (multiple) engine controllers and the fire zone to discharge condensate because the (multiple) engine controllers are positioned along a portion of the engine casing near the outside of the fire zone. Since discharging condensate into the fire zone is undesirable, a discharge assembly is used to remove condensate from the (multiple) bleed air ducts and discharge the condensate to an area outside the fire zone.

[0134] In addition, positioning the (multiple) engine controllers along the engine casing reduces the distance between the (multiple) engine controllers and the location from which bleed air is drawn from within the (multiple) bleed air ducts. The reduction in the distance between the (multiple) engine controllers and the location from which bleed air is drawn from within the (multiple) bleed air ducts in turn reduces the total distance that the (multiple) bleed air ducts extend. The reduction in the total distance that the (multiple) bleed air ducts extend in turn reduces the footprint / weight of the (multiple) bleed air ducts and reduces the pressure drop associated with bleed air moving a longer distance within the (multiple) bleed air ducts. The reduction in the pressure drop in turn means that the measured pressure, temperature, or a combination thereof of the bleed air is more accurate. The more accurate measurement in turn means that the (multiple) engine controllers can more effectively determine the operating parameters of the turbofan engine and adjust the operation of the turbofan engine accordingly.

[0135] As discussed herein, the size of the fire zone within a ducted turbofan engine is larger than, for example, the fire zone within a turbofan engine. The size of the fire zone in a ducted turbofan engine is such that routing the bleed air ducts to an area outside the fire zone to discharge condensate is not economically or physically (e.g., in terms of how much additional space is required) feasible. The discharge assembly is fluidly coupled to a portion of the bleed air duct that is disposed within the fire zone. However, the discharge assembly includes weep holes and a discharge duct that divert condensate to an area outside the fire zone.

[0136] To the extent not already described, the different features and structures of the various embodiments may be combined with or used in place of one another as desired. The fact that a feature is not illustrated in all embodiments is not to be construed as meaning that it cannot be so illustrated, but rather is done for the sake of brevity of description. Thus, the various features of the different embodiments may be mixed and matched as desired to form new embodiments, whether or not the new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure. Further, it will be understood that the specific discharge assemblies shown may all be used in a single turbofan engine and are not mutually exclusive.

[0137] This written description uses examples to describe aspects of the present disclosure described herein (including the best mode), and also enables any person skilled in the art to practice aspects of the present disclosure (including making and using any device or system, and performing any incorporated method). The patentable scope of aspects of the present disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. If such other examples have structural elements that are not different from the literal language of the claims, or if such other examples include equivalent structural elements that are not materially different from the literal language of the claims, then such other examples are intended to be within the scope of the claims.

[0138] Additional aspects are provided by the subject matter of the following clauses:

[0139] A turbomachine, comprising: an engine core including a compressor section, a combustor section, and a turbine section arranged in a series flow configuration and defining a stator, a rotor, and a fire zone; a fan section rotatably coupled to the rotor; an air bleed duct fluidly coupled to at least one of the fan section or the compressor section and having a gravity low point within the fire zone; and a drain assembly disposed at a joint along the air bleed duct, the drain assembly including a bleed hole fluidly coupled to the gravity low point and a drain duct fluidly coupled to the bleed hole and having an outlet external to the fire zone.

[0140] The turbomachine according to any of the preceding clauses, wherein the drain assembly includes a joint fitting that includes a joint.

[0141] The turbomachine according to any of the preceding clauses, wherein at least a portion of the bleed hole is formed within the joint fitting.

[0142] The turbomachine according to any of the preceding clauses, wherein the bleed hole is disposed within a bleed hole fitting coupled to the joint fitting.

[0143] The turbomachine according to any of the preceding clauses, wherein the drain duct is coupled to the joint fitting by at least one of welding, bonding, fastening, threading, or a combination thereof.

[0144] The turbomachine according to any of the preceding clauses, wherein the joint fitting is welded to the air bleed duct.

[0145] The turbomachine according to any of the preceding clauses, wherein the joint fitting includes a top and a stem, the top includes a first internal passage, the stem includes a second internal passage fluidly coupled to the first internal passage at the joint, and the top extends transversely to the stem.

[0146] The turbomachine according to any of the preceding clauses, wherein at least one air bleed duct is at least partially defined by the first internal passage.

[0147] A turbine engine according to any of the preceding clauses, wherein the bleed hole is disposed within the fire zone.

[0148] A turbine engine according to any of the preceding clauses, wherein the bleed hole is disposed external to the fire zone.

[0149] A turbine engine according to any of the preceding clauses, further comprising a bleed hole fitting, and wherein the bleed hole fitting defines an outlet of the discharge duct.

[0150] A turbine engine according to any of the preceding clauses, further comprising a combustible fluid leakage zone (FFLZ) and an engine controller, an extraction air duct extending into the FFLZ, the engine controller being disposed within the FFLZ and operably coupled to the extraction air duct.

[0151] A turbine engine according to any of the preceding clauses, wherein the engine controller is operably coupled to the extraction air duct downstream of the fluid at the junction.

[0152] A turbine engine according to any of the preceding clauses, wherein the engine controller measures at least one of temperature, pressure, or a combination thereof of the extraction air flow within the extraction air duct to determine at least one of pressure, temperature, or a combination thereof of the working air flow from the region of the turbine engine from which the extraction air flow within the extraction air duct is drawn.

[0153] A turbine engine according to any of the preceding clauses, wherein the engine controller is a full-authority digital engine controller (FADEC).

[0154] A turbine engine according to any of the preceding clauses, wherein the discharge assembly is included within a plurality of discharge assemblies, and the extraction air duct is included within a plurality of extraction air ducts.

[0155] A turbine engine according to any of the preceding clauses, wherein at least one of the plurality of discharge assemblies is fluidly coupled to two or more of the plurality of extraction air ducts.

[0156] A turbine engine according to any of the preceding clauses, wherein the discharge assembly is fluidly coupled to the extraction air duct at two or more junctions along the extraction air duct.

[0157] A turbine engine according to any of the preceding clauses, further comprising a nacelle surrounding the engine core, wherein the discharge duct discharges to the exterior of the nacelle.

[0158] A turbine engine according to any of the preceding clauses, wherein the fan section includes a plurality of fan blades extending outwardly from the nacelle.

[0159] A turbine engine according to any of the preceding clauses, wherein the emissions assembly includes a lip and a seat, the lip being receivable within the seat to couple together two portions of the emissions assembly.

[0160] A turbine engine according to any of the preceding clauses, wherein the lip is located along the emissions duct.

[0161] A turbine engine according to any of the preceding clauses, wherein the emissions assembly includes a bleed hole fitting, and wherein the seat is provided along the bleed hole fitting.

[0162] A turbine engine according to any of the preceding clauses, wherein the emissions assembly includes a joint fitting, and wherein the seat is provided along the joint fitting.

[0163] A turbine engine according to any of the preceding clauses, wherein the bleed hole is positioned at a length (L) from the joint, the length (L) being defined as the minimum straight-line distance between the starting point of the bleed hole and the nearest part of the joint, the emissions assembly having a joint fitting that has a first internal passage and a second internal passage, the second internal passage having a maximum diameter (D).

[0164] A turbine engine according to any of the preceding clauses, wherein the ratio between the length (L) and the maximum diameter (D) is greater than or equal to 4 and less than or equal to 8.

[0165] A turbine engine according to any of the preceding clauses, wherein the emissions assembly includes one of a joint fitting or a bleed hole fitting having a corresponding part with a bleed hole, wherein the emissions duct is threadedly connected to the corresponding part of the bleed hole fitting or the joint fitting.

[0166] A turbine engine according to any of the preceding clauses, wherein a first part of the bleed hole is defined by a first structure of the emissions assembly, and a second part of the bleed hole is defined by a second structure of the emissions assembly.

[0167] A turbine engine according to any of the preceding clauses, wherein the first structure is a joint fitting and the second structure is the emissions duct.

[0168] A turbine engine according to any of the preceding clauses, wherein the joint fitting is a T-joint.

[0169] A turbine engine according to any of the preceding clauses, wherein the joint fitting is a Y-joint.

[0170] A turbine engine according to any of the preceding clauses, further comprising a connection fitting extending between the joint fitting and the emissions duct.

[0171] A turbine engine according to any of the preceding clauses, further comprising a connection fitting extending between the bleed hole fitting and the emissions duct.

[0172] A turbine engine according to any of the preceding clauses, further comprising a connector at least partially surrounding the connection fitting.

[0173] A turbine engine according to any of the preceding clauses, wherein the bleed hole includes a funnel portion at the inlet of the bleed hole.

[0174] A turbine engine according to any of the preceding clauses, further comprising a bleed hole fitting, and wherein the bleed hole fitting defines an outlet of the discharge duct.

[0175] A turbine engine according to any of the preceding clauses, wherein the turbine engine is a ducted fan engine.

[0176] A ducted fan engine, comprising: an engine core including a compressor section, a combustor section, and a turbine section arranged in a series flow configuration and defining a stator, a rotor, and a combustion zone; a fan section rotatably coupled to the rotor; a bleed air duct fluidly coupled to at least one of the fan section or the compressor section and having a gravity low point within the combustion zone; and a discharge assembly disposed at a joint along the bleed air duct, the discharge assembly including a bleed hole fluidly coupled to the gravity low point and a discharge duct fluidly coupled to the bleed hole and having an outlet outside the combustion zone.

[0177] A ducted fan engine according to any of the preceding clauses, wherein the discharge assembly includes a joint fitting that includes a joint.

[0178] A ducted fan engine according to any of the preceding clauses, wherein at least a portion of the bleed hole is formed within the joint fitting.

[0179] A ducted fan engine according to any of the preceding clauses, wherein the bleed hole is disposed within a bleed hole fitting coupled to the joint fitting.

[0180] A ducted fan engine according to any of the preceding clauses, wherein the discharge duct is coupled to the joint fitting by at least one of welding, bonding, fastening, threading, or a combination thereof.

[0181] A ducted fan engine according to any of the preceding clauses, wherein the joint fitting is welded to the bleed air duct.

[0182] A ducted fan engine according to any of the preceding clauses, wherein the joint fitting includes a top and a stem, the top includes a first internal passage, the stem includes a second internal passage fluidly coupled to the first internal passage at the joint, and the top extends transversely to the stem.

[0183] A ducted fan engine according to any of the preceding clauses, wherein at least one bleed air duct is at least partially defined by the first internal passage.

[0184] A ducted fan engine according to any of the preceding clauses, wherein the bleed hole is provided within the fire zone.

[0185] A ducted fan engine according to any of the preceding clauses, wherein the bleed hole is provided outside the fire zone.

[0186] A ducted fan engine according to any of the preceding clauses, wherein the bleed hole defines an outlet of the discharge duct.

[0187] A ducted fan engine according to any of the preceding clauses, further comprising a combustible fluid leakage zone (FFLZ) and an engine controller, a bleed air duct extending into the FFLZ, the engine controller being disposed within the FFLZ and operably coupled to the bleed air duct.

[0188] A ducted fan engine according to any of the preceding clauses, wherein the engine controller is operably coupled to the bleed air duct downstream of the fluid at the joint.

[0189] A ducted fan engine according to any of the preceding clauses, wherein the engine controller measures at least one of the temperature, pressure, or a combination thereof of the bleed air flow within the bleed air duct to determine at least one of the pressure, temperature, or a combination thereof of the working air flow from the area of the ducted fan engine from which the bleed air flow within the bleed air duct is drawn.

[0190] A ducted fan engine according to any of the preceding clauses, wherein the engine controller is a full-authority digital engine controller (FADEC).

[0191] A ducted fan engine according to any of the preceding clauses, wherein the discharge assembly is included within a plurality of discharge assemblies, and the bleed air duct is included within a plurality of bleed air ducts.

[0192] A ducted fan engine according to any of the preceding clauses, wherein at least one of the plurality of discharge assemblies is fluidly coupled to two or more of the plurality of bleed air ducts.

[0193] A ducted fan engine according to any of the preceding clauses, wherein the discharge assembly is fluidly coupled to the bleed air duct at two or more joints along the bleed air duct.

[0194] A ducted fan engine according to any of the preceding clauses, further comprising a nacelle surrounding the engine core, wherein the discharge duct discharges to the outside of the nacelle.

[0195] A ducted fan engine according to any of the preceding clauses, wherein the fan section includes a plurality of fan blades extending outwardly from the nacelle.

[0196] A ducted fanless turbine engine according to any of the preceding clauses, wherein the discharge assembly includes a lip and a seat, and the lip can be received within the seat to couple two parts of the discharge assembly together.

[0197] A ducted fanless turbine engine according to any of the preceding clauses, wherein the lip is positioned along the discharge duct.

[0198] A ducted fanless turbine engine according to any of the preceding clauses, wherein the discharge assembly includes a bleed hole fitting, and the seat is provided along the bleed hole fitting.

[0199] A ducted fanless turbine engine according to any of the preceding clauses, wherein the discharge assembly includes a joint fitting, and the seat is provided along the joint fitting.

[0200] A ducted fanless turbine engine according to any of the preceding clauses, wherein the bleed hole is positioned at a length (L) from the joint, the length (L) being defined as the minimum straight-line distance between the starting point of the bleed hole and the nearest part of the joint, and the discharge assembly has a joint fitting that has a first internal passage and a second internal passage, and the second internal passage has a maximum diameter (D).

[0201] A ducted fanless turbine engine according to any of the preceding clauses, wherein the ratio between the length (L) and the maximum diameter (D) is greater than or equal to 4 and less than or equal to 8.

[0202] A ducted fanless turbine engine according to any of the preceding clauses, wherein the discharge assembly includes one of a joint fitting or a bleed hole fitting having a corresponding part with a bleed hole, and the discharge duct is threadedly connected to the corresponding part of the bleed hole fitting or the joint fitting.

[0203] A ducted fanless turbine engine according to any of the preceding clauses, wherein a first part of the bleed hole is defined by a first structure of the discharge assembly, and a second part of the bleed hole is defined by a second structure of the discharge assembly.

[0204] A ducted fanless turbine engine according to any of the preceding clauses, wherein the first structure is a joint fitting, and the second structure is a discharge duct.

[0205] A ducted fanless turbine engine according to any of the preceding clauses, wherein the joint fitting is a T-joint.

[0206] A ducted fanless turbine engine according to any of the preceding clauses, wherein the joint fitting is a Y-joint.

[0207] A ducted fanless turbine engine according to any of the preceding clauses, further comprising a connecting fitting extending between the joint fitting and the discharge duct.

[0208] A ducted fanless turbine engine according to any of the preceding clauses, further comprising a connection fitting extending between the bleed hole fitting and the discharge duct.

[0209] A ducted fanless turbine engine according to any of the preceding clauses, further comprising a connector at least partially surrounding the connection fitting.

[0210] A ducted fanless turbine engine according to any of the preceding clauses, wherein the bleed hole includes a funnel portion at an inlet of the bleed hole.

[0211] A ducted fanless turbine engine according to any of the preceding clauses, wherein the bleed hole includes a diffuser portion at an outlet of the bleed hole.

Claims

1. A turbine engine, comprising: An engine core including a compressor section, a combustor section, and a turbine section arranged in a series flow and defining a stator, a rotor, and a fire zone; A fan section rotatably coupled to the rotor; An air bleed duct fluidly coupled to at least one of the fan section or the compressor section and having a gravity low point within the fire zone; And A drain assembly disposed at a joint along the air bleed duct, the drain assembly including a bleed hole fluidly coupled to the gravity low point and a drain pipe fluidly coupled to the bleed hole and having an outlet outside the fire zone.

2. The turbine engine according to claim 1, wherein, The drain assembly includes a joint fitting, the joint fitting including the joint.

3. The turbine engine according to claim 2, wherein, At least a portion of the bleed hole is formed within the joint fitting.

4. The turbine engine according to claim 2, wherein, The bleed hole is disposed within a bleed hole fitting coupled to the joint fitting.

5. The turbine engine according to claim 4, wherein, The drain pipe is coupled to the joint fitting by at least one of welding, bonding, fastening, threading, or a combination thereof.

6. The turbomachine according to claim 2, wherein, The joint fitting is welded to the air bleed duct.

7. The turbomachine according to claim 2, wherein, The joint fitting includes a top and a stem, the top including a first internal passage, the stem including a second internal passage fluidly coupled to the first internal passage at the joint, the top extending transversely to the stem.

8. The turbine engine according to claim 7, wherein, At least one air bleed duct is at least partially defined by the first internal passage.

9. A turbine engine according to any one of claims 1 to 8, wherein, The bleed hole is disposed within the fire zone.

10. A turbine engine according to any one of claims 1 to 8, wherein, The bleed hole is disposed outside the fire zone.

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