|| List of recent Gas Turbine Engine-related patents
|Rotor disc with fluid removal channels to enhance life of spindle bolt|
A rotor disc configured to reduce the likelihood of fractures developing in spindle bolts in gas turbine engines is disclosed. The spindle bolts extend axially through the rotor disc to retain the rotor assembly in place in the gas turbine engine.
|Mounting system for mounting engine nacelle components and associated method|
The mounting system can be used in mounting a turbofan gas turbine engine having a nacelle including two halves, each half having a hinged end hingedly connected to the pylon and a free end lockingly engageable with the engine structure. The mounting system can include a primary connection connecting the engine structure to the pylon, and a flexible connection provided between the hinged connections and the pylon, the flexible connection being elastically deformed when a significant force is exerted in a transversal plane upon one of the halves in the closed position..
|Gas turbine engine and electrical system|
One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine.
|Shell and tiled liner arrangement for a combustor|
A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell.
|Microchannel systems and methods for cooling turbine components of a gas turbine engine|
The present application and the resultant patent thus provide a microchannel system for cooling a hot gas path surface of a turbine. The microchannel system may include a turbine component having an outer surface extending along a hot gas path of the turbine, a microchannel defined within the turbine component and extending about the outer surface, and a number of pockets defined within the turbine component and positioned along the microchannel.
|Gas turbine engine thermal management system|
A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan.
|Probalistic high cycle fatigue (hcf) design optimization process|
A novel probabilistic method for analyzing high cycle fatigue (hcf) in a design of a gas turbine engine is disclosed. The method may comprise identifying a component of the gas turbine engine for high cycle fatigue analysis, inputting parametric data of the component over a predetermined parameter space into at least one computer processor, using the at least one computer processor to build a plurality of flexible models of the component based on the parametric data of the component over the predetermined parameter space, using the at least one computer processor to build a plurality of emulators of the component based on the plurality of flexible models, and using the at least one computer processor to predict a probability of hcf based at least in part on the parametric data of the component over the predetermined parameter space and the plurality of emulators..
|Use of ss data trends in fault resolution process|
An automated method for resolving fault in an engine is disclosed. The method may include providing a reasoner module for recommending a set of maintenance actions to resolve fault in the engine, inputting steady state performance data from the engine into the reasoner module, and using the reasoner module to recommend a set of maintenance actions based at least in part on the steady state performance data.
|Low hub-to-tip ratio fan for a turbofan gas turbine engine|
A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge.
|Gas turbine engine vane assembly and method of mounting same|
The gas turbine engine vane assembly has a vane having an elongated airfoil body extending to a tip and a grommet disposed around the tip. An insert having a closed loop shape with an inner surface matingly shaped to receive the outer surface of the grommet, and an outer surface matingly shaped to be snugly received in the slot.
|Grain microstructure in dampers of gas turbine engine|
A damper for a gas turbine engine is provided. The damper comprises a first portion, a second portion, and a surface.
|Geared turbofan engine with integral gear and bearing supports|
A gas turbine engine includes a bearing. A bearing support includes a first wall that extends between the first and second ends and is operatively supported by the bearing at a first end.
|Gas turbine engine and electric machine|
An electric machine is disclosed integrated to rotate with a shaft of a gas turbine engine. In one form the electric machine is integrated with a fan of the gas turbine engine.
|Dampers for fan spinners of aircraft engines|
Dampers for fan spinners of aircraft engines are disclosed. An example fan module for a gas turbine engine may include a fan disk; fan blades mounted to the fan disk and extending radially therefrom; a fan spinner operatively coupled to the fan disk at an axially upstream position; and/or one or more elastic vibration dampers operatively interposing the fan spinner and the fan disk.
|Gas turbine engine heat exchanger system|
An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air.
|Gas turbine engine system and an associated method thereof|
A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor.
|Gas turbine engine and method of operating thereof|
A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine.
|Gas turbine efficiency and regulation speed improvements using supplementary air system continuous and storage systems and methods of using the same|
The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include additional heated compressed air injection, steam injection, water recovery, exhaust tempering, fuel heating, and stored heated air injection..
|Cooled cooling air system for a gas turbine|
In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.. .
|Gas turbine engine fuel system with ecology valve|
A gas turbine engine fuel system has an ecology valve for withdrawing residual fuel from primary and secondary fuel manifolds upon engine shut-down. The ecology valve has primary and secondary reservoirs respectively connected in fluid flow communication with the primary and secondary fuel manifolds.
|Exhaust diffuser for a gas turbine engine exhaust system|
An exhaust diffuser for a gas turbine engine includes a diffuser inlet, a diffuser exit, an inner diffuser wall, and an outer diffuser wall. The inner diffuser wall may include a first tubular member with a flared downstream portion.
|Airfoil cooling circuit|
An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit.
|Noise reducing vane|
A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region.
|Aircraft using turbo-electric hybrid propulsion system for multi-mode operation|
A vehicle incorporating a hybrid propulsion system. In one form, the vehicle may be an aircraft such that the system includes gas turbine engines as a first motive power source, and one or more battery packs as a second motive power source.
|Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events|
A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.. .
|Return fluid air cooler system for turbine cooling with optional power extraction|
In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply; and a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid.. .
|Method and system for combustion control between multiple combustors of gas turbine engine|
A system includes a first combustor having a first combustion chamber, a first head end with a first plurality of fuel nozzles, and a first effusion plate. The first effusion plate has a first plurality of openings for the first plurality of fuel nozzles, and the first effusion plate has a first plurality of openings configured to enable air flow into the first combustion chamber.
|Gas turbine engines with fuel injector assemblies|
In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem defining a fuel path for fuel and a flow guide coupled to and extending along the stem.
|Gas turbine engine sump pressurization system|
A sump pressurization system for a gas turbine engine comprises a first hollow shaft and a second hollow shaft disposed within the first hollow shaft and defining a cavity therebetween. Each of the first and second hollow shafts has a common axis of rotation.
|Article for high temperature service|
Articles for use at high temperatures, for example as gas turbine engine components, are described. The article includes a substrate and a coating disposed over the substrate.
|Gas turbine engine component|
The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein a primary gas channel for axial gas flow is defined between the elements (22), wherein the component (27) has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure (23) positioned internally of the inner ring (20) for transferring loads between said elements (22) and a bearing structure (24) for a turbine shaft (11) positioned centrally in the component (27), wherein the annular load transfer structure (23) extends circumferentially along at least a part of an inner side of the inner ring (20) and inwards in a radial direction of the component (27), wherein the annular load transfer structure (23) has a first portion (23a) and a second portion (23b), and wherein the first portion (23a) is located closer to the inner ring (20) than the second portion (23b). The invention is characterized in that the first portion (23a) is radially inclined between a first position (30) in the vicinity of the inner ring (20) and an axially displaced second position (31) and wherein the second portion (23b) extends from the second position (31) and is inclined in relation to the first portion (23a), and wherein the annular load transfer structure (23) is provided with a plurality of circumferentially spaced load carrying members (32) arranged at a side of the first portion (23a) axially facing in a direction towards the second position (31), wherein the load carrying members (32) are arranged to form a load carrying connection between the annular load transfer structure (23) and said elements (22) via the inner ring (20).
|Shroud arrangement for a gas turbine engine|
Described is a shroud arrangement for a gas turbine engine, comprising: a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a casing of the engine via at least one fore attachment and at least one aft attachment, the fore and aft attachment restricting radial movement of the seal segment relative to the engine casing; and, an axial restrictor which prevents axial movement of the seal segment relative to the engine casing, the axis being the principal rotational axis of the engine, wherein the fore and aft retention features are slidably engaged with a carrier segment or engine casing from a common direction. Also described is a gas turbine engine having the shroud arrangement..
|Shroud arrangement for a gas turbine engine|
A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path.
|Low pressure turbine provided with splitters at the last stator array, in particular for a gas turbine engine|
A low pressure turbine, in particular for a gas turbine engine, extends along an axis, has an annular conduit for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades, which define a plurality of spaces between them in circumferential direction; the spaces are split by respective splitters into a radially outer conduit and into a radially inner conduit; the radial position of the splitters is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit.. .
|Shroud arrangement for a gas turbine engine|
A seal segment for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits, wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous path between an inlet on the outboard side of the plate and an exhaust.. .
|Valve for gas turbine engine|
A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressurized source.
|Shroud arrangement for a gas turbine engine|
A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine..
|Heat exchange arrangement|
A heat exchange arrangement for a gas turbine engine. The arrangement includes a first conduit for an engine component cooling fluid and a second conduit for a second fluid.
|Flow sleeve for thermal control of a double-wall turbine shell and related method|
A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface.
|Gas turbine engine actuation systems including high temperature actuators and methods for the manufacture thereof|
Embodiments of a gas turbine engine actuation system are provided, as are embodiments of a high temperature actuator and methods for the manufacture thereof. In one embodiment, the gas turbine engine actuation system includes an actuated gas turbine engine component and a high temperature actuator, which has a rotor mechanically linked to the actuated gas turbine engine component and a stator surrounding at least a portion of the rotor.
|Turbine gear assembly support having symmetrical removal features|
A gas turbine engine includes a fan including a plurality of fan blades rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a geared architecture arranged in a housing and driven by the turbine section for rotating the fan about the axis, and a support member that supports the geared architecture within the gas turbine engine. The support member includes an inner portion and an outer portion.
|Internal detonation engine, hybrid engines including the same, and methods of making and using the same|
Hybrid internal detonation-gas turbine engines incorporating detonation or pulse engine technology (such as an internal detonation engine), and methods of manufacturing and using the same are disclosed. The internal detonation engine includes a detonation chamber having a fuel igniter therein, a stator at one end of the detonation chamber having at least a first opening to receive fuel, a rotor adjacent to the stator, and an energy transfer mechanism configured to convert energy from igniting or detonating the fuel to mechanical energy.
|Cavity swirl fuel injector for an augmentor section of a gas turbine engine|
A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.. .
|Electrical generation arrangement for an aircraft|
This invention relates to a multi-spool gas turbine engine, including: a first generator for providing electrical power to an electrical system, the generator being driveably connected to a first spool; a second generator for providing electrical power to the electrical system, the generator being driveably connected to a second spool; a disconnection device for disconnecting the second generator from the second spool; and, a controller configured to selectively operate the disconnection device under predetermined powered engine conditions.. .
|Gas turbine engine combustor with tailored temperature profile|
A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.. .
|Combustion nozzle with floating aft plate|
The present application provides a combustion nozzle for use with a gas turbine engine. The combustion nozzle may include a number of mixing tubes, an outer shell surrounding the mixing tubes, and a floating aft plate assembly.
|Combustor skin assembly for gas turbine engine|
A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.. .
|Liquid fuel turbine engine for reduced oscillations|
A gas turbine engine may include a plurality of pilot fuel supply lines configured to supply liquid fuel. Each pilot fuel supply line may be coupled to a respective fuel injector.
|Gas turbine engine combustor with integrated combustor vane|
A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.. .
|Aircraft propulsion gas turbine engine with heat exchange|
One embodiment of the present invention is a unique aircraft propulsion gas turbine engine. Another embodiment is a unique gas turbine engine.
|Gas turbine engines having plasma flow-controlled intake systems|
Embodiments of a gas turbine engine (“gte”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a gte. In one embodiment, the gte includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section.
|Acoustic damping system for a combustor of a gas turbine engine|
An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor.
|Providing oxidation to a gas turbine engine|
A gas turbine engine includes a compressor for compressing air from an environment; a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel; a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor; and an injector coupled with a source of oxidizer for injecting the oxidizer into the combustor. A method for operating a gas turbine engine includes compressing air from an environment; receiving the compressed air at a combustor; mixing the compressed air with fuel; injecting oxidizer into the combustor in addition to the air from the environment; combusting the fuel with the compressed air and the oxidizer; receiving exhaust gas from the combusted fuel; and powering the compression of the air from the environment using the exhaust gas..
|Air regulation for film cooling and emission control of combustion gas structure|
A gas turbine engine compressed air flow control arrangement, including: a combustion gas structure having an acceleration geometry (20) configured to receive combustion gas (18) from a can combustor and accelerate the combustion gas (18) to a speed appropriate for delivery onto a first row of turbine blades, the combustion gas structure defining a straight combustion flow path; a film cooling hole (58) disposed through the combustion gas structure at a location within or downstream of the acceleration geometry (20); a sleeve (64) surrounding at least a portion of the combustion gas structure comprising the film cooling hole and defining a volume (62) between the combustion gas structure and the sleeve (64); and an adjustable flow control system configured to adjust a flow volume between the plenum (44) and the volume (62).. .
A method of balancing a set of retaining and locking plates used to retain a row of gas turbine engine aerofoil blades in attachment to a rotor disc, includes: (i) providing a weighing plate having a circular track; (ii) providing a non-rotating, static balancing apparatus capable of detecting unbalance in the weighing plate; (iii) positioning the weighing plate on the static balancing apparatus, and positioning the set of retaining and locking plates on the track in an arrangement corresponding to a possible arrangement for the set of plates in use in the engine; and (iv) repositioning the retaining and locking plates on the track to arrive at a balanced arrangement for the set of plates.. .
|High purity powders|
This invention relates to high purity yttria or ytterbia stabilized zirconia powders comprising from about 0 to about 0.15 weight percent impurity oxides, from about 0 to about 2 weight percent hafnium oxide (hafnia), from about 6 to about 25 weight percent yttrium oxide (yttria) or from about 10 to about 36 weight percent ytterbium oxide (ytterbia), and the balance zirconium oxide (zirconia). Thermal barrier coatings for protecting a component such as blades, vanes and seal surfaces of gas turbine engines, made from the high purity yttria or ytterbia stabilized zirconia powders, have a density greater than 88% of the theoretical density with a plurality of verticalza macrocracks homogeneously dispersed throughout the coating to improve its thermal fatigue resistance..
|Borescope inspection port fitting|
A borescope inspection (bsi) port fitting is provided for a gas turbine engine. The borescope inspection (bsi) port fitting includes a housing with a borescope inspection port..
|Aircraft electrical system|
An aircraft electrical network including a first starter generator mechanically coupled to a first shaft of an aircraft main engine. The first starter generator is configured to turn the first shaft of the main engine in a starting mode, and to generate electricity from the first shaft of the gas turbine engine in a generating mode.
|Shrouded pilot liquid tube|
A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an injector of a gas turbine engine while the shroud remains fixed to pilot liquid fuel conduit..
|Inner premix tube air wipe|
An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion.
|Self-cooling loop with electric ram fan for motor driven compressor|
A motor driven compressor system includes a motor with an internal cooling loop. The internal cooling loop draws cooling air from outside the motor driven compressor system.
|System for distributing compressed air in a combustor|
A system for distributing compressed air in a combustor of a gas turbine engine. The system may include a flow splitter, a center duct, an outer duct, and an inner duct configured to separate and receive compressed air from a prediffuser exit, and to route separate flows of the compressed air to separate downstream locations for the combustion reaction and for cooling.
|Outer premix barrel vent air sweep|
A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes.
|Tapered gas turbine engine liquid gallery|
A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body spanning from a first end to a second end in a circumferential direction.
|Pivoting swirler inlet valve plate|
A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape.
|Lean fuel intake gas turbine engine|
A lean fuel intake gas turbine engine includes a compressor to compress a working gas at a concentration equal to or lower than the flammable limit concentration to thereby generate a compressed gas, a catalytic combustor to burn the compressed gas through a catalytic reaction, a turbine driven by a combustion gas from the catalytic combustor, a heat exchanger to heat, by means of an exhaust gas from the turbine, the compressed gas that is introduced from the compressor into the catalytic combustor, a heat exchanger bypass valve to communicate between inlet and outlet sides of the heat exchanger, a first catalyst outlet temperature control unit to open the heat exchanger bypass valve in the event that the outlet temperature of the catalytic combustor attains a value equal to or higher than an outlet prescribed value.. .
|Turbine engine shutdown temperature control system with an elongated ejector|
A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing.
|Apparatus and method for measurement of the film cooling effect produced by air cooled gas turbine components|
A method for measurement of a film cooling effect is disclosed. Film cooling is a technique developed to protect gas turbine engine components from the extremely high temperatures created during its operation.
|Electro-magnetic coupling system|
An electro-magnetic coupling system for transferring torque between a pair of coaxial spools of a gas turbine engine is provided. The system includes a first rotor rotatable with one of the spools, a second rotor rotatable with the other of the spools, and a stator.
|System reliability analysis and management using physics-based models embedded in a baysian network|
A method for assessing reliability in a gas turbine engine system includes using a processor to carry out instructions from a memory to propagate a physics-based model through a bayesian network to assess reliability for the gas turbine engine system. A system for assessing reliability for a gas turbine engine system includes a memory including instructions to propagate a physics-based model through a bayesian network to assess reliability for a gas turbine engine system.
|Airfoil edge form transfer grinding tool|
A grinding tool is provided that includes an axial grinding wheel having a circumferential cutting slot formed therein, the cutting slot having a cross-sectional profile that includes a floor having a first radius of curvature, a first side wall rising upward from the floor and having a second radius of curvature, a second side wall rising upward from the floor opposite the first side wall and having a third radius of curvature. At least one radius of curvature corresponds to a surface, such as a leading edge of a gas turbine engine airfoil..