Patent Description:
In various conditions, such as during testing and development, aircraft gas turbine engines may require measurement of operational parameters such as pressures and temperatures of fluids within engine flow paths (e.g., a core flow path). Accordingly, sensors such as pressure and temperature "rakes" may be installed within the fluid flow paths to measure the desired fluid parameters. However, during some operational conditions, the sensors may experience icing or ingestion of undesirable fluids (e.g., oil) which may inhibit the accurate measurement of fluid parameters. To prevent icing and fluid ingestion on similar types of sensor equipment, conductive or inductive heating systems along with physical shielding have been used. However, the introduction of electrical conductive/inductive heating systems adds additional complexity to sensor systems and requires the routing of electrical wiring through extensive portions of the gas turbine engine. Additionally, the electrical wiring may require shielding to prevent degradation by extreme conditions (e.g., high temperatures) within the gas turbine engine. Furthermore, physical shielding may not be sufficiently effective at preventing fluid ingestion by sensors. Accordingly, there is a need for improved sensor systems which address one or more of the above-noted concerns. <CIT> and <CIT> disclose an arrangement of the prior art.

According to an aspect of the invention a measurement system for an aircraft gas turbine engine, according to claim <NUM>, includes a probe and a heated-gas source in fluid communication with the probe. The probe includes a probe body extending lengthwise along a probe axis. The probe body defines an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The plurality of sensor inlet ports is axially spaced along the probe axis. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extends from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.

In an optional embodiment of any of the aspects or embodiments described above and herein, each sensor inlet port of the plurality of sensor inlet ports faces a common fluid flow direction.

In an optional embodiment of any of the aspects or embodiments described above and herein, the measurement system further includes sensor instrumentation in fluid communication with the plurality of sensor inlet ports via the plurality of probe conduits. The sensor instrumentation is configured to receive the sensed fluid flow and calculate one or more sensed fluid flow measurements.

In an optional embodiment of any of the aspects or embodiments described above and herein, the measurement system further includes at least one first valve in fluid communication with the plurality of probe conduits. The at least one first valve is operable between a sensing valve position and a heating valve position, wherein: the at least one first valve is configured to allow passage of the sensed fluid flow from the plurality of sensor inlet ports to the sensor instrumentation in the sensing valve position and the at least one first valve is configured to allow passage of the heated gas flow from the heated-gas source to the plurality of sensor inlet ports in the heating valve position.

In an optional embodiment of any of the aspects or embodiments described above and herein, the probe includes at least one heated-gas channel located in the interior of the probe body and in fluid communication with the heated-gas source.

In an optional embodiment of any of the aspects or embodiments described above and herein, the at least one heated-gas channel is located within the internal cavity of the probe.

In an optional embodiment of any of the aspects or embodiments described above and herein, the probe body includes at least one perforation extending through the probe body from the internal cavity to the exterior of the probe body.

In an optional embodiment of any of the aspects or embodiments described above and herein, the at least one heated-gas channel is located within and defined by the probe body.

In an optional embodiment of any of the aspects or embodiments described above and herein, the probe includes at least one heated-gas channel located in the interior of the probe body and in fluid communication with the heated-gas source via at least one second valve and independent of the at least one first valve.

In an optional embodiment of any of the aspects or embodiments described above and herein, the measurement system further includes a controller configured to control the heated gas flow from the heated-gas source to the probe.

In an optional embodiment of any of the aspects or embodiments described above and herein, the controller is configured to regulate the heated gas flow to the probe, cased on one or both of a measured pressure and a measured temperature of the sensed fluid flow, to achieve a target temperature of the probe.

In an optional embodiment of any of the aspects or embodiments described above and herein, each sensor inlet port of the plurality of sensor inlet ports includes a Kiel probe or a Pitot probe.

According to another aspect of the invention, a gas turbine engine for an aircraft includes a probe located within a fluid flow path of the gas turbine engine, according to claim <NUM>.

In an optional embodiment of any of the aspects or embodiments described above and herein, the gas turbine engine further includes a duct defining the fluid flow path. The probe is mounted to the duct within the fluid flow path.

In an optional embodiment of any of the aspects or embodiments described above and herein, the gas turbine engine further includes a compressor. The compressor defines the heated-gas source and supplies compressor bleed gas to the probe as the heated gas flow.

According to another aspect of the invention, a method for operating a measurement system for an aircraft gas turbine engine , according to claim <NUM>, includes receiving a sensed fluid flow with a plurality of sensor inlet ports extending through a probe body of a probe. The probe body defines an internal cavity of the probe. The method further includes supplying a heated gas flow, with a heated-gas source in fluid communication with the probe, to one or both of: the plurality of sensor inlet ports via a plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extends from the respective sensor inlet port to an exterior of the probe body.

In an optional embodiment of any of the aspects or embodiments described above and herein, the step of receiving the sensed fluid flow with the plurality of sensor inlet ports includes receiving the sensed fluid flow with sensor instrumentation in fluid communication with the plurality of sensor inlet ports via the plurality of probe conduits and calculating one or more sensed fluid flow measurements with the sensor instrumentation.

In an optional embodiment of any of the aspects or embodiments described above and herein, the method further includes operating at least one valve in fluid communication with the plurality of probe conduits between a sensing valve position and a heating valve position, operating the at least one valve including: positioning the at least one valve in the sensing valve position during the step of receiving the sensed fluid flow with the plurality of sensor inlet ports to allow passage of the sensed fluid flow from the plurality of sensor inlet ports to the sensor instrumentation and positioning the at least one valve in the heating valve position during the step of supplying the heated gas flow to allow passage of the heated gas flow from the heated-gas source to the plurality of sensor inlet ports.

In an optional embodiment of any of the aspects or embodiments described above and herein, the step of supplying the heated gas flow includes supplying the heated gas flow to at least one heated-gas channel located in the interior of the probe body with the heated-gas source.

In an optional embodiment of any of the aspects or embodiments described above and herein, the method further includes regulating the heated gas flow to the probe, based on one or both of a measured pressure and a measured temperature of the sensed fluid flow, to achieve a target temperature of the probe.

The present disclosure, and all its aspects, embodiments and advantages associated therewith will become more readily apparent in view of the detailed description provided below, including the accompanying drawings.

Referring to <FIG>, an exemplary gas turbine engine <NUM> is schematically illustrated. The gas turbine engine <NUM> is disclosed herein as a two-spool turbofan engine that generally includes an inlet <NUM>, a fan section <NUM>, a compressor section <NUM>, a combustor section <NUM>, a turbine section <NUM>, and an exhaust section <NUM>. The fan section <NUM> drives air along a bypass flow path <NUM> while the compressor section <NUM> drives air along a core flow path <NUM> for compression and communication into the combustor section <NUM> and then expansion through the turbine section <NUM>. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiments, it should be understood that the concepts described herein are not limited to use with turbofans or even to gas turbine engines, as the teachings may be applied to other types of turbine engines or to other types of aircraft engines such as rotary engines. Additionally, it is further contemplated that aspects of the present disclosure may be applied to other engines (e.g., gas turbine engines) or industrial equipment which are not associated with aircraft or with the aerospace field, in general.

The gas turbine engine <NUM> generally includes a low-pressure spool <NUM> and a high-pressure spool <NUM> mounted for rotation about a longitudinal centerline <NUM> of the gas turbine engine <NUM> relative to an engine static structure <NUM> via one or more bearing systems <NUM>. It should be understood that various bearing systems <NUM> at various locations may alternatively or additionally be provided.

The low-pressure spool <NUM> generally includes a first shaft <NUM> that interconnects a fan <NUM>, a low-pressure compressor <NUM>, and a low-pressure turbine <NUM>. The first shaft <NUM> is connected to the fan <NUM> through a gear assembly of a fan drive gear system <NUM> to drive the fan <NUM> at a lower speed than the low-pressure spool <NUM>. The high-pressure spool <NUM> generally includes a second shaft <NUM> that interconnects a high-pressure compressor <NUM> and a high-pressure turbine <NUM>. It is to be understood that "low pressure" and "high pressure" or variations thereof as used herein are relative terms indicating that the high pressure is greater than the low pressure. An annular combustor <NUM> is disposed between the high-pressure compressor <NUM> and the high-pressure turbine <NUM> along the longitudinal centerline <NUM>. The first shaft <NUM> and the second shaft <NUM> are concentric and rotate via the one or more bearing systems <NUM> about the longitudinal centerline <NUM> which is collinear with respective longitudinal centerlines of the first and second shafts <NUM>, <NUM>.

Airflow along the core flow path <NUM> is compressed by the low-pressure compressor <NUM>, then the high-pressure compressor <NUM>, mixed and burned with fuel in the combustor <NUM>, and then expanded over the high-pressure turbine <NUM> and the low-pressure turbine <NUM>. The low-pressure turbine <NUM> and the high-pressure turbine <NUM> rotationally drive the low-pressure spool <NUM> and the high-pressure spool <NUM>, respectively, in response to the expansion.

During gas turbine engine operation, development, testing, and/or certification, it may be necessary to measure fluid flow parameters, such as pressure or temperature, inside one or more fluid (e.g., air or other gas) flow paths of the gas turbine engine. Fluid flow parameters may be measured at various stages of a gas turbine engine such as the gas turbine engine <NUM>. For example, fluid flow parameters may be measured in portions of the gas turbine engine <NUM> such as, but not limited to, the inlet <NUM>, the compressor section <NUM> including various stages of the compressors <NUM>, <NUM>, the exhaust section <NUM>, and other portions of the gas turbine engine <NUM> along the core flow path <NUM> or the bypass flow path <NUM>.

Referring to <FIG>, gas turbine engine <NUM> may include at least one pressure measurement system <NUM> configured to measure the fluid flow parameters at a respective at least one fluid flow path location of the gas turbine engine <NUM>. In some embodiments, the pressure measurement system <NUM> includes a pressure probe <NUM> configured to be disposed in a fluid flow path <NUM> of the gas turbine engine <NUM> to sample fluid (e.g., sensed fluid flow) within the fluid flow path <NUM>. Alternatively, in some other embodiments, the pressure probe <NUM> may be positioned external to the gas turbine engine <NUM>, for example, to measure fluid flow parameters of ambient air outside of the gas turbine engine <NUM> and/or along a body or wings of an aircraft and/or to measure fluid flow parameters in aircraft systems not associated with the gas turbine engine <NUM> such as, for example, within air ducts of an aircraft HVAC system. The pressure probe <NUM> includes a probe body <NUM> extending lengthwise along a probe axis <NUM>. The probe body <NUM> defines an internal cavity <NUM> of the pressure probe <NUM>. The pressure probe <NUM> may be used to measure a total pressure (sometimes referred to as "stagnation pressure" or "pitot pressure") of the fluid within the fluid flow path <NUM>. Constituents of total pressure, such as the static pressure and the dynamic pressure (also known as "velocity pressure") of the fluid, may additionally be determined using the pressure probe <NUM>. For ease of description the system <NUM> and probe <NUM> will be referred to as the "pressure measurement system" <NUM> and the "pressure probe" <NUM>, respectively. However, it should be understood that the pressure measurement system <NUM> and pressure probe <NUM> may be used to additionally or alternatively measure fluid flow parameters other than pressure such as, but not limited to fluid flow swirl, fluid temperature, and fluid flow velocity.

The pressure probe <NUM> includes a plurality of sensor inlet ports <NUM> extending through the probe body <NUM> and may be configured as a "rake" with the plurality of sensor inlet ports <NUM> axially spaced along the probe axis <NUM>. In various embodiments, the plurality of sensor inlet ports <NUM> may be substantially aligned with a fluid flow direction <NUM> of the fluid traversing the fluid flow path <NUM>. In other words, each sensor inlet port of the plurality of sensor inlet ports <NUM> may face a common fluid flow direction (e.g., the fluid flow direction <NUM>). In various other embodiments, the sensor inlet ports of the plurality of sensor inlet ports <NUM> may face different directions from one another depending, for example, on the expected fluid flow direction <NUM> of the fluid traversing the fluid flow path <NUM>. For example, where the fluid experiences voracity or rotation along the fluid flow path <NUM>, such that the fluid flow direction <NUM> varies, the plurality of sensor inlet ports <NUM> may be configured to face different directions to accommodate the varying fluid flow direction <NUM>. In various embodiments, the sensor inlet ports of the plurality of sensor inlet ports <NUM> may be configured as Pitot probes (also known as a "Pitot tubes"). The sensor inlet ports may be configured as Kiel probes, which are a variation of the Pitot probes having an inlet protected by a "shroud," thereby making the Kiel probe configuration less sensitive to changes in yaw angle. Accordingly, the Kiel probe configuration may be more useful when the sensor inlet port alignment with the fluid flow direction <NUM> is variable or imprecise, for example, in comparison to conventional Pitot probe configurations. However, the present disclosure is not limited to any particular configuration of the plurality of sensor inlet ports <NUM>.

As previous discussed, fluid flow parameters may be measured at various stages of a gas turbine engine such as the gas turbine engine <NUM>. For example, fluid flow parameters may be measured in portions of the gas turbine engine <NUM> such as, but not limited to, the inlet <NUM>, the compressor section <NUM> including various stages of the compressors <NUM>, <NUM>, the exhaust section <NUM>, other portions of the gas turbine engine <NUM> along the core flow path <NUM> or the bypass flow path <NUM>, etc. Accordingly, pressure probes, such as the pressure probe <NUM>, may be located to measure fluid flow parameters at one or more locations within the gas turbine engine <NUM>, such as the previously discussed exemplary locations. The present disclose, however, is not limited to any particular location of the pressure probe <NUM> within a gas turbine engine, and the pressure probe <NUM> may be located at any position within a gas turbine engine to measure fluid flow parameters associated with a fluid flow along a fluid flow path, such as the fluid flow path <NUM>. As shown in <FIG> and <FIG>, in various embodiments, the pressure probe <NUM> may be mounted to a duct <NUM> (e.g., a duct defining a portion of the bypass flow path <NUM>) or other mounting structure of the gas turbine engine <NUM> which defines all or a portion of the fluid flow path <NUM>. The pressure probe <NUM> may, therefore, extend outward from the duct <NUM> and into the fluid flow path <NUM> such that the plurality of sensor inlet ports <NUM> are configured to be located within and facing the fluid traversing the fluid flow path <NUM> in the fluid flow direction <NUM>. The pressure probe <NUM> is illustrated in <FIG> as extending radially inward from a mounting position on the duct <NUM>, however, the present disclosure is not limited to any particular orientation of the pressure probe <NUM> within the fluid flow path <NUM> or with respect to the duct <NUM> or other mounting structure.

Referring to <FIG>, <FIG>, and <FIG>, the pressure measurement system <NUM> includes sensor instrumentation <NUM> in fluid communication with the plurality of sensor inlet ports <NUM>. The sensor instrumentation <NUM> is configured to receive the sensed fluid flow (illustrated in <FIG>, <FIG>, and <FIG> as sensed fluid flow <NUM>) and to calculate one or more sensed fluid flow measurements such as, but not limited to, total pressure, static pressure, dynamic pressure, fluid flow velocity, fluid temperature, etc. As shown in <FIG>, <FIG>, and <FIG>, the sensor instrumentation <NUM> is located outside of the pressure probe <NUM> and may be located internal or external to the gas turbine engine <NUM>.

The pressure measurement system <NUM> includes a plurality of probe conduits <NUM> fluidly connecting the plurality of sensor inlet ports <NUM> to the sensor instrumentation <NUM>. For example, each probe conduit of the plurality of probe conduits <NUM> may be coupled to a respective sensor inlet port of the plurality of sensor inlet ports <NUM> and may extend from the respective sensor inlet port to an exterior of the probe body <NUM>. As shown, for example, in <FIG>, each probe conduit of the plurality of probe conduits <NUM> may include an internal conduit portion <NUM> located inside the probe body <NUM> and an external conduit portion <NUM> located outside the probe body <NUM> which connects the internal conduit portion <NUM> to one or more external components, such as the sensor instrumentation <NUM>.

During operation of a gas turbine engine, such as the gas turbine engine <NUM>, for operation, testing, etc., ice, water, sleet, and other liquids (e.g., oil, fuel, etc.) may accumulate on the pressure probe <NUM> as well as on and/or inside the plurality of sensor inlet ports <NUM>, thereby impeding accurate measurement of fluid flow parameters with the pressure probe <NUM>. Accordingly, the pressure probe <NUM> may require protection against icing and/or fluid ingestion in order to prevent or minimize a loss of fluid flow parameter measurement accuracy.

Referring to <FIG>, the pressure measurement system <NUM> may include a heated-gas source <NUM> in fluid communication with the pressure probe <NUM> and configured to supply a heated gas flow (illustrated in <FIG> as heated gas flow <NUM>) to the pressure probe <NUM>. In various embodiments, for example, the heated-gas source <NUM> may be configured to supply heated gas <NUM> to each sensor inlet port of the plurality of sensor inlet ports <NUM> via respective probe conduits of the plurality of probe conduits <NUM> and/or to the interior of the probe body outside of and independent of the plurality of probe conduits <NUM>. In various embodiments, the heated-gas source <NUM> may be a component of the gas turbine engine <NUM> which is configured to generate heated-gas as a byproduct of the normal operation of the component. For example, the heated-gas source <NUM> may be one of the compressors <NUM>, <NUM> of the gas turbine engine <NUM>, which may provide compressor bleed air to the pressure probe <NUM> as the heated gas <NUM>. Where the pressure measurement system <NUM> is located in one of the compressors <NUM>, <NUM> (see <FIG>) or in proximity thereto, the length of the plurality of probe conduits <NUM> may be minimal. In various other embodiments, the heated-gas source <NUM> may be specifically configured to supply heated gas <NUM> to the pressure probe <NUM> and may be located internal or external to the gas turbine engine <NUM>. For clarity, <FIG> and <FIG> schematically illustrate exemplary flow paths of the sensed fluid flow <NUM> and the heated gas flow <NUM> for a single sensor inlet port of the plurality of sensor inlet ports <NUM>, and the present disclosure will describe the flow paths of the sensed fluid flow <NUM> and the heated gas flow <NUM> for a single sensor inlet port. However, it should be understood that the other sensor inlet ports of the plurality of sensor inlet ports <NUM> may be configured similarly. Additionally, in <FIG>, portions of fluid conduits, such as the plurality of probe conduits <NUM>, have been omitted to more clearly illustrate the flow paths for the sensed fluid flow <NUM> and the heated gas flow <NUM>.

Referring to <FIG>, in various embodiments, the pressure measurement system <NUM> may include at least one first valve <NUM> in fluid communication with the plurality of probe conduits <NUM>. The at least one first valve <NUM> may be configured as a three-way valve as shown, for example, in <FIG>. However, the present disclosure is not limited to this particular configuration of the at least one first valve <NUM>. Each first valve of the at least one first valve <NUM> may be fluidly connected within the external conduit portion <NUM> of each respective probe conduit of the plurality of probe conduits <NUM> so as to control fluid flow between the pressure probe <NUM>, the heated-gas source <NUM>, and the sensor instrumentation <NUM>. The at least one first valve <NUM> is operable between a sensing valve position and a heating valve position. In the sensing valve position, the at least one first valve <NUM> allows passage of the sensed fluid flow <NUM> through the probe conduit <NUM> from the sensor inlet port <NUM> to the sensor instrumentation <NUM> and prevents the passage of the heated gas flow <NUM> through the probe conduit <NUM> from the heated-gas source <NUM> to the sensor inlet port <NUM>. In the heating valve position, the at least one first valve <NUM> allows passage of the heated gas flow <NUM> through the probe conduit <NUM> from the heated-gas source <NUM> to the sensor inlet port <NUM> and prevents the passage of the sensed fluid flow <NUM> through the probe conduit <NUM> from the sensor inlet port <NUM> to the sensor instrumentation <NUM>.

In an exemplary operation of the pressure measurement system <NUM> shown in <FIG> and described above, the at least one first valve <NUM> may initially be positioned to the heating valve position to supply heated gas flow <NUM> to the sensor inlet port <NUM> from the heated-gas source <NUM>. Application of the heated gas flow <NUM> to the sensor inlet port <NUM> may provide an "anti-icing" function by heating the sensor inlet port <NUM> and/or the probe body <NUM> sufficiently so that ice does not form on the sensor inlet port <NUM> and/or the probe body <NUM>. Application of the heated gas flow <NUM> to the sensor inlet port <NUM> may additionally provide a "de-icing" function by heating the sensor inlet port <NUM> and/or the probe body <NUM> sufficiently so that any ice that has previously formed on the sensor inlet port <NUM> and/or the probe body <NUM> is melted. Further, the exhaust of the heated gas flow <NUM> from the sensor inlet port <NUM> may prevent or substantially reduce the ingestion of undesired fluids such as, but not limited to. water, fuel, and oil, into the sensor inlet port <NUM>. This "anti-ingestion" feature of the pressure measurement system <NUM> may be especially useful where the pressure probe <NUM> is located in air/oil cavities of the gas turbine engine <NUM> where oil may otherwise be ingested into the sensor inlet port <NUM>. In various embodiments, the heated-gas source <NUM> may be operated to control a flow rate and/or a temperature of the heated gas flow <NUM> supplied to the sensor inlet port <NUM>. When it is necessary to measure fluid flow parameters with the pressure probe <NUM>, the at least one first valve <NUM> may be repositioned to the sensing valve position, thereby cutting off the heated gas flow <NUM> to the sensor inlet port <NUM> and allowing the sensed fluid flow <NUM> from the fluid flow path <NUM> to be measured by the sensor instrumentation <NUM>. Once measurement of the fluid flow parameters has been completed, the at least one first valve <NUM> may again be positioned to the heating valve position, thereby resuming the anti-icing, de-icing, and/or anti-ingestion functions of the pressure measurement system <NUM>.

Referring to <FIG>, in various embodiments, the pressure probe <NUM> includes at least one heated-gas channel <NUM> located in the interior of the probe body <NUM> and in fluid communication with the heated-gas source <NUM>. For example, the at least one heated-gas channel <NUM> may extend within the internal cavity <NUM> of the pressure probe <NUM> or may be formed within the probe body <NUM> itself. The at least one heated-gas channel <NUM> is independent of the plurality of probe conduits <NUM> used to convey the sensed fluid flow <NUM> to the sensor instrumentation <NUM>. The heated gas flow <NUM> may be supplied to the at least one heated-gas channel <NUM> by at least one external conduit <NUM> in fluid communication between the heated-gas source <NUM> and the at least one heated-gas channel <NUM>.

As shown in <FIG>, in various embodiments, the at least one heated gas channel <NUM> may be located within the internal cavity <NUM> of the pressure probe <NUM> to provide the heated gas flow <NUM> to the internal cavity <NUM>, thereby heating the probe body <NUM> and plurality of sensor inlet ports <NUM>. In a first example of the at least one heated-gas channel <NUM> (indicated as heated-gas channel 600A in <FIG>), the heated-gas channel 600A extends through a portion of internal cavity <NUM>. The heated-gas channel 600A may extend substantially axially through the internal cavity <NUM> relative to the probe axis <NUM>. In various embodiments, the heated-gas channel 600A may include a plurality of exit apertures <NUM> spaced (e.g., axially spaced) from one another along a length of the heated gas channel 600A within the internal cavity <NUM>, in order to more equally distribute the heated gas flow <NUM> within the internal cavity <NUM>. In a second example of the at least one heated-gas channel <NUM> (indicated as heated-gas channel 600B in <FIG>), the heated-gas channel 600B is in fluid communication with the internal cavity <NUM> but may not substantially extend into the internal cavity <NUM>. In various embodiments, the at least one heated-gas channel <NUM> may include a plurality of heated-gas channels which may be the same as or different from one another. For example, the at least one heated-gas channel <NUM> may include one or more of the exemplary heated-gas channel 600A and/or one or more of the exemplary heated-gas channel 600B. The present disclosure is not limited to the above-described exemplary configurations of the at least one heated-gas channel <NUM> and other suitable heated-gas channel configurations may be used based on the size, shape, and heating requirements of the particular respective pressure probe. In various embodiments, the probe body <NUM> may include at least one perforation <NUM> extending through the probe body <NUM> from the internal cavity <NUM> to the exterior of the probe body <NUM>, thereby allowing the heated-gas flow <NUM> to exit the pressure probe <NUM>.

As shown in <FIG>, in various embodiments, the at least one heated-gas channel <NUM> may be located within and defined by the probe body <NUM>. The at least one heated-gas channel <NUM> may be formed within the probe body <NUM> during formation of the probe body <NUM>, for example, using an additive manufacturing process. Accordingly, the heated gas flow <NUM> may pass through the at least one heated-gas channel <NUM> within the probe body <NUM>, thereby warming the probe body <NUM>. The at least one heated-gas channel <NUM> may include at least one exit aperture <NUM> allowing the heated gas flow <NUM> to exit the at least one heated-gas channel <NUM>. As shown in <FIG>, the at least one exit aperture <NUM> may extend between the at least one heated-gas channel <NUM> and an exterior of the probe body <NUM>. In various other embodiments, the at least one exit aperture <NUM> may extend between the at least one heated-gas channel <NUM> and the internal cavity <NUM> of the pressure probe <NUM>. The heated gas flow <NUM> may then exit the pressure probe <NUM>, for example, via the at least one perforation <NUM>, as shown in <FIG>. In various embodiments, the pressure probe <NUM> may include multiple configurations of the at least one heated-gas channel <NUM>, such as the internally formed at least one heated-gas channel <NUM> of <FIG>. in combination with the at least one heated-gas channel <NUM> configurations (e.g., heated-gas channel 600A, 600B) of <FIG>.

As shown in <FIG> and <FIG>, the pressure measurement system <NUM> may include at least one second valve <NUM> in fluid communication with the at least one heated-gas channel <NUM>. Each second valve of the at least one second valve <NUM> may be fluidly connected within the external conduit <NUM> so as to control fluid flow between the heated-gas source <NUM> and the at least one heated-gas channel <NUM>. The at least one second valve <NUM> is operable between a heating valve position and a secured valve position. In the heating valve position, the at least one second valve <NUM> allows passage of the heated gas flow <NUM> through the external conduit <NUM> from the heated-gas source <NUM> to the at least one heated-gas channel <NUM>. In the secured valve position, the at least one second valve <NUM> prevents passage of the heated gas flow <NUM> through the external conduit <NUM> from the heated-gas source <NUM> to the at least one heated-gas channel <NUM>.

In an exemplary operation of the pressure measurement system <NUM> shown in <FIG> and <FIG> and described above, the at least one second valve <NUM> may initially be positioned to the heating valve position to supply heated gas flow <NUM> to the at least one heated-gas channel <NUM> from the heated-gas source <NUM>, thereby heating the probe body <NUM> and/or the plurality of sensor inlet ports <NUM>. Accordingly, the heated gas flow <NUM> may provide anti-icing and de-icing functionality to the pressure probe <NUM>. In comparison to the pressure measurement system <NUM> shown in <FIG> and described above, embodiments of the pressure measurement system <NUM> shown in <FIG> and <FIG> do not supply the heated gas flow <NUM> to the plurality of sensor inlet ports <NUM> via the plurality of probe conduits <NUM> and, therefore, do not provide anti-ingestion functionality. However, the configuration of the <FIG> and <FIG> embodiments of the pressure measurement system <NUM> may allow for the continuous application of the heated gas flow <NUM> to the pressure probe <NUM>, and thereby the anti-icing and de-icing functionality, such as during measurement of the fluid flow parameters. By using independent fluid flow paths for the sensed fluid flow <NUM> and the heated gas flow <NUM>, the sensed fluid flow <NUM> may be supplied to the sensor instrumentation <NUM> without securing the heated gas flow <NUM> to the pressure probe <NUM>. In various embodiments, the heated-gas source <NUM> may be operated to control a flow rate and/or a temperature of the heated gas flow <NUM> supplied to the pressure probe <NUM>.

Referring to <FIG>, in various embodiments, the pressure measurement system <NUM> may include a combination of features discussed above with respect to embodiments of <FIG>. For example, as shown in <FIG>, the pressure measurement system <NUM> may include the at least one first valve <NUM> configured to control the heated gas flow <NUM> from the heated-gas source <NUM> to the sensor inlet port <NUM> and the sensed fluid flow from the sensor inlet port <NUM> to the sensor instrumentation <NUM> as well as the at least one second valve <NUM> configured to control the heated gas flow <NUM> from the heated-gas source <NUM> to the at least one heated-gas channel <NUM> of the pressure probe <NUM>.

Referring to <FIG>, the present disclosure pressure measurement system <NUM> may include a controller <NUM> in communication with one or more of the components (e.g., the at least one first valve <NUM>, the at least one second valve <NUM>, the heated-gas source <NUM>, the sensor instrumentation <NUM>, etc.) that may be present in the various embodiments of the present disclosure pressure measurement system <NUM>. For example, the controller <NUM> may be configured to control the heated gas flow <NUM> from the heated-gas source <NUM> to the pressure probe <NUM>. The controller <NUM> may be configured to execute stored instructions (e.g., algorithmic instructions) that cause the pressure measurement system <NUM> to perform steps or functions described herein. The controller <NUM> may include any type of computing device, computational circuit, or any type of process or processing circuit capable of executing a series of instructions that are stored in memory. The controller <NUM> may include multiple processors and/or multicore CPUs and may include any type of processor, such as a microprocessor, digital signal processor, co-processors, a micro-controller, a microcomputer, a central processing unit, a field programmable gate array, a programmable logic device, a state machine, logic circuitry, analog circuitry, digital circuitry, etc., and any combination thereof. The instructions stored in memory may represent one or more algorithms for controlling the pressure measurement system <NUM> as described herein, and the stored instructions are not limited to any particular form (e.g., program files, system data, buffers, drivers, utilities, system programs, etc.) provided they can be executed by the controller <NUM>. The controller <NUM> memory may be a non-transitory machine-readable storage medium configured to store instructions that when executed by one or more processors, cause the one or more processors to perform or cause the performance of certain functions. The memory may be a single memory device or a plurality of memory devices. The present disclosure controller <NUM> is not limited to any particular type of memory device. One skilled in the art will appreciate, based on a review of this disclosure, that the implementation of the controller <NUM> may be achieved via the use of hardware, software, firmware, or any combination thereof. Communications between pressure measurement system <NUM> components may be by wired connection or may be by wireless communication, or any combination thereof. Further, in various embodiments, the sensor instrumentation <NUM> may be included as part of the controller <NUM>.

In various embodiments, the controller <NUM> may be configured to regulate (e.g., modulate) the heated-gas flow <NUM> to the pressure probe <NUM> to achieve a target temperature of the pressure probe <NUM>. For example, the controller <NUM> may control the position of the at least one first valve <NUM>, the position of the at least one second valve <NUM>, and/or the flow rate and/or temperature of the heated gas flow <NUM> provided by the heated-gas source <NUM> to achieve the target temperature of the pressure probe <NUM>. The target temperature for the pressure probe <NUM> may be determined, for example, based on one or both of a measured pressure (e.g., static pressure) or a measured temperature of the fluid in the fluid flow path <NUM>, as calculated by the sensor instrumentation <NUM>.

It is noted that various connections are set forth between elements in the preceding description and in the drawings. It is noted that these connections are general and, unless specified otherwise, may be direct or indirect and that this specification is not intended to be limiting in this respect. A coupling between two or more entities may refer to a direct connection or an indirect connection. An indirect connection may incorporate one or more intervening entities. It is further noted that various method or process steps for embodiments of the present disclosure are described in the following description and drawings. The description may present the method and/or process steps as a particular sequence. However, to the extent that the method or process does not rely on the particular order of steps set forth herein, the method or process should not be limited to the particular sequence of steps described. As one of ordinary skill in the art would appreciate, other sequences of steps may be possible. Therefore, the particular order of the steps set forth in the description should not be construed as a limitation.

As used herein, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

While various aspects of the present disclosure have been disclosed, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the present invention.

Claim 1:
A measurement system for an aircraft gas turbine engine, the measurement system comprising:
a probe (<NUM>) comprising:
a probe body (<NUM>) extending lengthwise along a probe axis (<NUM>), the probe body (<NUM>) defining an internal cavity (<NUM>) of the probe;
a plurality of sensor inlet ports (<NUM>) extending through the probe body (<NUM>) and configured to receive a sensed fluid flow, the plurality of sensor inlet ports (<NUM>) axially spaced along the probe axis (<NUM>); and characterized by
a plurality of probe conduits (<NUM>), each probe conduit (<NUM>) of the plurality of probe conduits (<NUM>) coupled to a respective sensor inlet port (<NUM>) of the plurality of sensor inlet ports (<NUM>) and extending from the respective sensor inlet port (<NUM>) to an exterior of the probe body (<NUM>); and by the measurement system comprising
a heated-gas source (<NUM>) in fluid communication with the probe (<NUM>) and configured to supply a heated gas flow to one or both of:
the plurality of sensor inlet ports (<NUM>) via the plurality of probe conduits (<NUM>); and
an interior of the probe body (<NUM>) outside of the plurality of probe conduits (<NUM>).