Patent Description:
The present disclosure relates generally to gas turbine engines, and more particularly to a sensor system of a gas turbine engine.

A gas turbine engine typically includes a high pressure spool, a combustion system, and a low pressure spool disposed within an engine case to form a generally axial, serial flow path about the engine centerline. The high pressure spool includes a high pressure turbine, a high pressure shaft extending axially forward from the high pressure turbine, and a high pressure compressor connected to a forward end of the high pressure shaft. The low pressure spool includes a low pressure turbine, which is disposed downstream of the high pressure turbine, a low pressure shaft, which typically extends coaxially through the high pressure shaft, and a fan connected to a forward end of the low pressure shaft, forward of the high pressure compressor. The combustion system is disposed between the high pressure compressor and the high pressure turbine and receives compressed air from the compressors and fuel provided by a fuel injection system. A combustion process is carried out within the combustion system to produce high energy gases to produce thrust and turn the high and low pressure turbines, which drive the compressor and the fan to sustain the combustion process.

An engine control system for the gas turbine engine can employ sensors that relay data relating to various properties of the engine and its operation. For example, the engine control system may want to know the working fluid temperature and pressure at particular points in the engine. These properties are measured by probes that are communicatively connected to the engine control system. The probes have a particular size, though, which occupies space and adds weight to the engine. In addition, the positioning of the probes can affect the flow of the working fluid, which can affect the measurements of other probes. <CIT> relates to a pressure and temperature probe.

A probe is provided in claim <NUM> and includes a probe head, a probe tip extending from the probe head and ending with a sensor face in fluidic communication with a first fluid stream, a pressure channel extending into the probe tip through the sensor face, a pressure sensor configured to sense a pressure in the pressure channel, a temperature channel extending into the probe tip through the sensor face with a temperature orifice located on the sensor face and at least one exit port distal from the sensor face, and a temperature sensor configured to sense a temperature in the temperature channel. The temperature channel extends parallel to the pressure channel and is fluidly separate from the pressure channel. The temperature channel is configured to channel a fluid flow from the temperature orifice to the at least one exit port, which is configured to discharge the fluid flow into a second fluid stream.

A gas turbine engine extending along an axis is provided in claims <NUM> and <NUM>, and includes a fan section having a number of rotor cascades and a number of stator cascades, a splitter downstream of the fan section and having an inner side, an outer side, and an inside surface, a compressor section downstream of the fan section, a combustor section downstream of the compressor section, a turbine section downstream of the combustor section and connected to the compressor and/or fan sections, and a probe assembly located on the compressor and/or fan section and configured to sense a pressure and a total temperature of a first airflow stream. The probe includes a probe head, a probe tip extending from the probe head and ending with a sensor face in fluidic communication with a first fluid stream, a pressure channel extending into the probe tip through the sensor face, a pressure sensor configured to sense a pressure in the pressure channel, a temperature channel extending into the probe tip through the sensor face with a temperature orifice located on the sensor face and at least one exit port distal from the sensor face, and a temperature sensor configured to sense a temperature in the temperature channel. The temperature channel extends parallel to the pressure channel and is fluidly separate from the pressure channel. The temperature channel is configured to channel a fluid flow from the temperature orifice to the at least one exit port, which is configured to discharge the fluid flow into a second fluid stream.

<FIG> is a schematic side cross-section view of gas turbine engine <NUM>. Although <FIG> depicts a gas turbine engine typically used for aircraft propulsion, the present disclosure is readily applicable to gas turbine generators and other similar systems incorporating rotor-supported, shaft-driven turbines. Shown in <FIG> are gas turbine engine <NUM>, fan <NUM>, fan rotor cascades 13A - 13C, fan stator cascades 14A - 14D, high pressure compressor (HPC) <NUM>, combustor section <NUM>, high pressure turbine (HPT) <NUM>, low pressure turbine (LPT) <NUM>, struts <NUM>, fan case <NUM>, HPC case <NUM>, HPT case <NUM>, LPT case <NUM>, low pressure shaft <NUM>, high pressure shaft <NUM>, splitter <NUM>, inside surface <NUM>, injectors <NUM>, HPT blades <NUM>, LPT blades <NUM>, support rotor <NUM>, vane airfoil sections <NUM>, probe assembly <NUM>, engine control unit <NUM>, inlet air A, fan air AF, primary air AP, secondary air AS, and longitudinal engine centerline axis CL. Gas turbine engine <NUM> can be described as having cold section <NUM> and hot section <NUM>, as annotated in <FIG>.

In the illustrated embodiment, gas turbine engine <NUM> comprises a dual-spool turbofan engine in which the advantages of the present disclosure are particularly well illustrated. Gas turbine engine <NUM>, of which the operational principles are well known in the art, comprises cold section <NUM>, including fan <NUM> and HPC <NUM>, and hot section <NUM>, including combustor section <NUM>, HPT <NUM>, and LPT <NUM>. These components are each concentrically disposed around longitudinal engine centerline axis CL. Fan <NUM> is separated from HPC <NUM> by a plurality of struts <NUM>, and fan <NUM> is enclosed at its outer diameter within fan case <NUM>. Likewise, the other engine components are correspondingly enclosed at their outer diameters within various engine casings, including HPC case <NUM>, HPT case <NUM>, and LPT case <NUM>. Fan <NUM> is connected to LPT <NUM> through low pressure shaft <NUM>, and together with fan <NUM>, LPT <NUM>, and low pressure shaft <NUM>, comprise the low pressure spool. HPC <NUM> is connected to HPT <NUM> through high pressure shaft <NUM>, and together HPC <NUM>, HPT <NUM>, and high pressure shaft <NUM> comprise the high pressure spool.

During normal operation, inlet air A enters engine <NUM> at fan <NUM>. Fan <NUM> comprises fan rotor cascades 13A-13C which are rotated by LPT <NUM> through low pressure shaft <NUM> (either directly as shown or through a gearbox, not shown). In conjunction with fan stator cascades 14A-14D (between which fan rotor cascades 13A-13C are positioned, respectively), fan air AF is accelerated and compressed. At splitter <NUM>, fan air AF is divided into streams of primary air AP (also known as gas path air) and secondary air AS (also known as bypass air). Secondary air AS produces a major portion of the thrust output of engine <NUM> while primary air AP is directed into HPC <NUM>. HPC <NUM> includes pluralities of rotors and stators, alternately positioned, that incrementally step up the pressure of primary air AP. HPC <NUM> is rotated by HPT <NUM> through high pressure shaft <NUM> to provide compressed air to combustor section <NUM>. The compressed air is delivered to combustor section <NUM>, along with fuel through injectors <NUM>, such that a combustion process can be carried out to produce the high energy gases necessary to turn HPT <NUM> and LPT <NUM>. Primary air AP continues through gas turbine engine <NUM> whereby it is typically passed through an exhaust nozzle to further produce thrust.

After being compressed in HPC <NUM> and participating in a combustion process in combustor section <NUM> to increase pressure and energy, primary air AP flows through HPT <NUM> and LPT <NUM> such that HPT blades <NUM> and LPT blades <NUM> extract energy from the flow of primary air AP. Primary air AP impinges on HPT blades <NUM> to cause rotation of high pressure shaft <NUM>, which turns HPC <NUM>. Primary air AP also impinges on LPT blades <NUM> to cause rotation of support rotor <NUM> and low pressure shaft <NUM>, which turns the rotating components of fan <NUM>.

In addition, gas turbine engine <NUM> includes probe assembly <NUM>. Probe assembly <NUM> begins exterior to fan case <NUM> and HPC case <NUM>, extends through one of struts <NUM> and splitter <NUM>, terminating flush with inside surface <NUM> of splitter <NUM> in fluid contact with primary air AP adjacent to the wall at the probe face. Thereby, probe assembly <NUM> can measure the static pressure and total temperature of primary air AP (i.e., the static primary air AP temperature plus the kinetic energy of primary air AP). Probe assembly <NUM> is communicatively connected to engine control unit (ECU) <NUM> such that ECU <NUM> receives measurements from probe assembly <NUM>. In the illustrated embodiment, probe assembly <NUM> is positioned downstream of fan rotor cascades 13A-13C and fan stator cascades 14A-14D and upstream of HPC <NUM>, although in alternate embodiments, probe assembly <NUM> can be positioned in other locations, such as within HPC <NUM> or amongst fan rotor cascades <NUM> and fan stator cascades <NUM>. Probe assembly <NUM> can also be referred to as a probe.

The components and configuration of gas turbine engine <NUM> as shown in <FIG> allow for ECU <NUM> to know the total temperature and static pressure of primary air AP as reported by probe assembly <NUM>. ECU <NUM> can then use this information to control gas turbine engine <NUM> appropriately. Depicted in <FIG> is one embodiment of the present disclosure, to which there are alternative embodiments. For example, engine <NUM> can be a three spool engine. In such an embodiment, engine <NUM> has an intermediate compressor between fan <NUM> and HPC <NUM> and an intermediate turbine between HPT <NUM> and LPT <NUM>, wherein the intermediate compressor is connected to the intermediate turbine with an additional shaft.

<FIG> is a schematic side cross-sectional view of gas turbine engine <NUM> proximate a probe assembly <NUM>. Also shown in <FIG> are inner side <NUM> and outer side <NUM>. At splitter <NUM>, fan air AF is divided into streams of primary air AP, flowing on inner side <NUM>, and secondary air AS, flowing on outer side <NUM>. Probe assembly <NUM> comprises probe head <NUM> with probe tip <NUM> extending therefrom. At the innermost end of probe tip <NUM> is sensor face <NUM> which is tangent to inside surface <NUM> of splitter <NUM>. Thereby, probe tip <NUM> extends at an acute, upstream angle from the flow of primary air AP. In the illustrated embodiment sensor face <NUM> is flat, although in alternate embodiments sensor face <NUM> can be curved to closer match the contour of splitter <NUM>. In addition, sensor face <NUM> is substantially flush with inside surface <NUM> of splitter <NUM> in that no part of sensor face <NUM> is more than <NUM> (<NUM> inch) from being even with inside surface <NUM>.

Probe assembly <NUM> also includes pressure sensor <NUM>, located in probe head <NUM>, and temperature sensor <NUM>, located in probe tip <NUM>. Pressure sensor <NUM> and temperature sensor <NUM> are each located within a respective channel (not shown in <FIG>) and will be described in more detail later in <FIG>. In the illustrated embodiment, probe assembly <NUM> is positioned on fan case <NUM> and configured to sense a pressure and a total temperature of primary air AP (i.e., the primary airflow stream). In some embodiments temperature sensor <NUM> can be located near (i.e., proximate) sensor face <NUM>, while in other embodiments, temperature sensor <NUM> can be located some distance away from sensor face <NUM> within a temperature channel. As will be shown and described later in <FIG>, a flow of fluid past temperature sensor <NUM> can result in a more accurate indication of total temperature of primary air AP. Pressure sensor <NUM> can be a pressure transducer that measures the static pressure of primary air AP, and temperature sensor <NUM> can be a resistive temperature detector, such as a contact thermometer, that measures the total temperature of primary air AP. The data from pressure sensor <NUM> and temperature sensor <NUM> is fed to ECU <NUM>. Because the properties are measured at the boundary of the flow of primary air AP, ECU <NUM> can do calculations to estimate the average properties of primary air AP across the primary air flowpath. In other embodiments, pressure sensor <NUM> can be routed elsewhere in or near ECU <NUM> by using a pneumatic line (not shown) leading from probe assembly <NUM> to a remote pressure transducer, thereby providing fluid communication between probe assembly <NUM> and a remote pressure transducer. This embodiment could be advantageous for harsh environments.

The components and configuration of gas turbine engine <NUM> allow for the static pressure and total temperature of primary air AP to be measured without the measurement devices protruding into the flowpath which prevents major flow disturbances due to probe assembly <NUM>. In addition, the static pressure and total temperature data can be transmitted to ECU <NUM> for further processing and can be used to control gas turbine engine <NUM>. In some embodiments, because of the flush mounted configuration, the sensed temperature differs from the center flow Ap total temperature. This is due to the incomplete Ap flow recovery as the flow comes to theoretical rest at the wall, and also due to wall heat conduction. A correction can be applied to account for this difference using empirical data or approximations based on flow velocity at the probe interface.

<FIG> is a cross-sectional front view of probe tip <NUM> along line <NUM>-<NUM> in <FIG>. Shown in <FIG> are HPC case void <NUM>, inner side <NUM>, outer side <NUM>, inside surfaces 39A, 39B, probe assembly <NUM>, probe tip <NUM>, probe shaft <NUM>, sensor face <NUM>, pressure sensor <NUM>, temperature sensor <NUM>, pressure channel <NUM>, pressure orifice <NUM>, temperature channel <NUM>, temperature orifice <NUM>, wires <NUM>, shaft <NUM>, and exit port <NUM>. Also labeled in <FIG> are primary air AP, secondary air AS, temperature channel flow F, probe tip diameter D<NUM>, pressure orifice diameter D<NUM>, temperature orifice diameter D<NUM>, exit port diameter D<NUM>, probe shaft diameter D<NUM>, and spacing S. In the illustrated embodiment, HPC case void <NUM> is a region between primary air AP and secondary air AS, being defined by respective inside surfaces 39A and 39B, as shown in <FIG>. Probe assembly <NUM> shown in the illustrated embodiment is not drawn to scale, in order to provide a sufficient level of detail. In a practical embodiment, the length of probe shaft <NUM> (i.e., in a direction of pressure channel <NUM> and temperature channel <NUM>) will be much greater than depicted. Pressure orifice <NUM> and temperature orifice <NUM> are each located on sensor face <NUM> in fluidic communication with primary air AP. Pressure channel <NUM> and temperature channel <NUM> are beside each other, extending through probe tip <NUM> along substantially parallel axes (not labeled), with the center of pressure channel <NUM> being approximately aligned with the center of temperature channel <NUM> relative to the CL axis of engine <NUM>, and with pressure channel <NUM> and temperature channel <NUM> being approximately perpendicular to Ap flow. Pressure channel <NUM> begins at pressure orifice <NUM> in sensor face <NUM> and extends all of the way to probe head <NUM> (shown in <FIG>). Pressure channel <NUM> is in fluidic communication with pressure sensor <NUM>. Thereby, primary air AP enters and can exert a static pressure on pressure channel <NUM>, the static pressure being measured by pressure sensor <NUM>.

Temperature channel <NUM> begins at temperature orifice <NUM> in sensor face <NUM> and also extends toward probe head <NUM>. Primary air AP entering temperature orifice <NUM> becomes temperature channel flow F, flowing through temperature channel <NUM> from temperature orifice <NUM>, past temperature sensor <NUM>, and out exit port <NUM> into secondary air AS. In the illustrated embodiment, exit port <NUM> is located in secondary air AS on outer side <NUM>, shown in <FIG>, and is oriented laterally (i.e., perpendicular to centerline axis CL, shown in <FIG>). In some embodiments, more than one exit port <NUM> can be used. The location of one or more exit ports will be shown and described in more detail later, in <FIG>, and <FIG>. During operation of gas turbine engine <NUM>, temperature channel flow F is driven by a pressure differential from temperature orifice <NUM> in primary air AP and exit port <NUM> in secondary air AS. Temperature sensor <NUM> electronically communicates with probe head <NUM> via wires <NUM>. Temperature sensor <NUM> further includes shaft <NUM> which extends into temperature channel <NUM> minimally contacting probe tip <NUM>, which thermally isolates shaft <NUM> from probe tip <NUM>. The flow of primary air AP can be affected by pressure orifice <NUM> and/or temperature orifice <NUM>. In order to prevent interference of the flow into one orifice by the other orifice, the center of pressure orifice <NUM> is at the same axial location as the center of temperature orifice <NUM>. In the illustrated embodiment, probe tip diameter D<NUM> is about <NUM> (<NUM> inch), pressure orifice diameter D<NUM> is about <NUM> (<NUM> inch), temperature orifice diameter D<NUM> is about <NUM> (<NUM> inch), and exit port diameter D<NUM> is about <NUM> (<NUM> inch). In the illustrated embodiment, probe tip <NUM> and probe shaft <NUM> are both circular in cross-sectional shape, with probe shaft diameter D<NUM> being slightly less than probe tip diameter D<NUM>. In some embodiments, probe tip <NUM> and/or probe shaft <NUM> can have cross-sectional shapes that are non-round. Different configurations for probe shaft <NUM>, including exemplary cross-sectional shapes, will be shown and described in more detail later, in <FIG>, and <FIG>. In a typical embodiment, pressure orifice <NUM> is spaced laterally apart from temperature orifice <NUM>, because temperature channel flow F through temperature channel <NUM> can be significant, thereby potentially disrupting the static pressure at pressure orifice <NUM>. Spacing S between the proximate sides of pressure orifice <NUM> and temperature orifice <NUM> is between about <NUM> - <NUM> times temperature orifice diameter D<NUM>. In the illustrated embodiment, spacing S is about <NUM> (<NUM> inch). The components and configuration of probe assembly <NUM> allow for the static pressure and total temperature of primary air AP to be measured by a single, compact device. In addition, the measurements can be taken accurately without the flow at pressure channel <NUM> being disturbed by the flow of primary air AP into temperature channel <NUM>.

<FIG> is a cross-sectional top view of probe shaft <NUM> shown in <FIG> along line 4A - 4A. Temperature channel flow F exits temperature channel <NUM> through exit port <NUM>. Secondary air AS flowing past probe shaft <NUM> having probe shaft diameter D<NUM> can be modeled as airflow over a cylinder, whereby surface pressure (i.e., pressure at a surface of probe shaft <NUM>) is lowest at points perpendicular to the direction of secondary air AS. Bernoulli's principle is known in the fluid arts as explaining this phenomenon. Accordingly, exit port <NUM> is located at a point on past probe shaft <NUM> that discharges temperature channel flow F in a direction that is about perpendicular to secondary air AS. Therefore, temperature sensor <NUM> of probe assembly <NUM> can be used to measure temperature of primary air AP even in an embodiment where the static pressures of primary air AP and secondary air AS are about the same because of the aforementioned effect.

As noted above in the description of <FIG>, other configurations of probe shaft <NUM> and/or exit port <NUM> are possible. <FIG> is a cross-sectional top view of a second embodiment of probe shaft <NUM> shown in <FIG> along line 4A - 4A. Temperature channel flow F through temperature channel <NUM> through exit ports <NUM> and 170A, each located opposite the other and configured to discharge exit port flow F', each being about half the flow of temperature channel flow F. <FIG> depicts an exemplary embodiment of probe assembly <NUM> having two exit ports <NUM>, 170A from temperature channel <NUM>. In some embodiments, three or more exit ports can be used on temperature channel <NUM>. In various embodiments, exit ports can be located at various radial positions around probe shaft <NUM>, with the positions being selected to achieve a desired temperature channel flow F for a design operating condition of gas turbine engine <NUM>. Additionally, exit port diameter D<NUM> and/or the radial locations of exit ports can also be changed in different embodiments to achieve a desired temperature channel flow F. Several factors can be considered in determining an optimum temperature channel flow F for a particular embodiment, in order to optimize the performance of temperature probe <NUM> (i.e., the performance of temperature sensor <NUM>). For example, a small value of temperature channel flow F can result in a slow response time, whereas a large value of temperature channel flow F can increase recovery error, which is the difference between the probe's measured air temperature and total air temperature.

<FIG> is a cross-sectional top view of a third embodiment of probe shaft <NUM> shown in <FIG> along line 4A - 4A. Temperature channel flow F exits temperature channel <NUM> through exit port <NUM> in a direction that is perpendicular to that of secondary air AS flowing past probe shaft <NUM>. In the illustrated embodiment, probe shaft <NUM> has a cross-sectional shape that is elliptical, and can be characterized by major dimension M and minor dimension L, as labeled. In the illustrated embodiment, a ratio of major dimension M to minor dimension L is about <NUM>. In some embodiments, the ratio of major dimension M to minor dimension L can range from about <NUM> - <NUM>. In other embodiments, the ratio of major dimension M to minor dimension L can be greater than <NUM>. In yet other embodiments, the cross-sectional shape of probe shaft <NUM> can be oval, oblong, egg-shaped, or any other non-circular geometric shape. Probe shaft <NUM> having a non-round cross-sectional shape can be particularly beneficial in some embodiments in defining a flow and/or pressure profile of secondary air AS (i.e., secondary airflow) over probe shaft <NUM>. Moreover, the flow and/or pressure profile of secondary air AS in the vicinity of exit port <NUM> can be particularly beneficial in some embodiments. Other exemplary cross-sectional shapes of probe shaft <NUM> will be shown and described later, in <FIG>.

<FIG> is a cross-sectional top view of a fourth embodiment of probe shaft <NUM> shown in <FIG> along line 4A - 4A. Temperature channel flow F through temperature channel <NUM> through exit ports <NUM> and 370A on probe shaft <NUM>, each located opposite the other and configured to discharge exit port flow F', each being about half the flow of temperature channel flow F. The description of the cross-sectional shape of probe shaft <NUM> is substantially similar to that provided above in regard to <FIG>. The descriptions of exit ports <NUM> and 370A, including various embodiments thereof, are substantially similar to those provided above in regard to <FIG>.

<FIG> is a cross-sectional top view of a fifth embodiment of probe shaft <NUM> shown in <FIG> along line 4A - 4A. Temperature channel flow F exits temperature channel <NUM> through exit port <NUM> in a direction that is perpendicular to that of secondary air AS flowing past probe shaft <NUM>. In the illustrated embodiment, probe shaft <NUM> has an asymmetrical airfoil cross-sectional shape, with exit port <NUM> being located on the "lift" side (i.e., high speed, reduced pressure side) of probe shaft <NUM>. In the illustrated embodiment, temperature channel flow F exits temperature channel <NUM> through exit port <NUM> in a direction that is perpendicular to that of secondary air AS flowing past probe shaft <NUM> on the "lift" side of the airfoil shape (i.e., near the side of lower relative pressure). In other embodiments, one or more exit ports can be located at other positions around the perimeter of probe shaft <NUM>. In various embodiments, the cross-sectional shape of probe shaft <NUM> and/or the location of one or more exit ports <NUM> can be selected to provide a desired temperature channel flow F based on a particular operating condition of gas turbine engine <NUM>. In some embodiments, the cross-sectional shape of probe shaft <NUM> can causes an appreciable "lift" force that can result in a lateral force on probe shaft <NUM> during the operation of gas turbine engine <NUM>. Accordingly, the materials and structural design of probe shaft <NUM> must be able to accommodate the "lift" force that results from an asymmetrical cross-sectional shape.

<FIG> is a cross-sectional top view of a sixth embodiment of probe shaft <NUM> shown in <FIG> along line 4A - 4A. Temperature channel flow F exits temperature channel <NUM> through exit port <NUM> in a direction that is perpendicular to that of secondary air AS flowing past probe shaft <NUM>. In the illustrated embodiment, probe shaft <NUM> has a symmetrical airfoil cross-sectional shape (i.e., symmetrical about axis <NUM> that is perpendicular to the flow direction of secondary air AS). This can also be referred to as a symmetrical airfoil, or as having a teardrop cross-sectional shape. A benefit of a symmetrical airfoil shape is that a high velocity of secondary air AS can be developed at the vicinity of exit port <NUM>, while not developing a "lift" force that can cause a lateral force on probe shaft <NUM> (as described in regard to probe shaft <NUM> shown in <FIG>). In other embodiments, one or more exit ports can be located at other positions around the perimeter of probe shaft <NUM>. In various embodiments, the cross-sectional shape of probe shaft <NUM> and/or the location of one or more exit ports <NUM> can be selected to provide a desired temperature channel flow F based on a particular operating condition of gas turbine engine <NUM>. As described above in regard to <FIG>, various non-round cross-sectional shapes can be particularly beneficial in some embodiments in defining the flow and/or pressure profiles of secondary air AS (i.e., secondary airflow) over probe shaft <NUM>, etc. and/or in the vicinity of exit ports <NUM>, etc. All non-round cross-sectional shapes of probe shaft <NUM> are within the scope of the present disclosure. Moreover, all configurations of exit ports <NUM> with regard to number, size, and/or placement on probe shaft <NUM> are within the scope of the present disclosure.

<FIG> is a cross-sectional front view of a second embodiment of probe assembly <NUM> shown in <FIG> along line <NUM> - <NUM>. Shown in <FIG> are HPC case void <NUM>, inner side <NUM>, outer side <NUM>, inside surfaces 39A, 39B, probe assembly <NUM>, probe shaft <NUM>, sensor face <NUM>, pressure sensor <NUM>, temperature sensor <NUM>, pressure channel <NUM>, pressure orifice <NUM>, temperature channel <NUM>, temperature orifice <NUM>, wires <NUM>, shaft <NUM>, and exit port <NUM>, all having a description substantially similar to that provided above in regard to <FIG>. In the illustrated embodiment, temperature sensor <NUM> is located higher in temperature channel <NUM> (i.e., further away from sensor face <NUM>), nearer exit port <NUM> than temperature sensor shown in <FIG>. Accordingly, temperature sensor <NUM> measures the temperature of temperature channel flow F at a point much nearer exit port <NUM> than in the embodiment shown in <FIG>. An advantage of probe assembly <NUM> is that a much shorter shaft <NUM> is required to support temperature sensor <NUM>, which can provide greater structural stability of temperature sensor <NUM>. This can be beneficial in an embodiment where temperature probe <NUM> is susceptible to vibration, flow turbulence, and the like. However, temperature sensor <NUM> can experience a time lag, particularly when the temperature of primary air AP is changing rapidly, as a result of the transport time of temperature channel flow F through temperature channel <NUM> from temperature orifice <NUM> to temperature sensor <NUM>.

Temperature probe <NUM>, <NUM> of the present disclosure measures temperature of a primary air AP using temperature sensor <NUM>, <NUM> that is recessed in temperature channel <NUM>, etc. (i.e., recessed from the primary air AP stream) because of channel flow F through temperature channel <NUM>, etc. Channel flow F is induced by a pressure differential between temperature orifice <NUM>, <NUM> in primary air AP and exit port <NUM>, <NUM> in secondary air AS. Primary air AP can be referred to as a first stream, and secondary air AS can be referred to as a second stream. Accordingly, a pressure differential between the first stream and the second stream induces channel flow F through temperature channel <NUM>, etc. In some embodiments, the first stream can be at a higher pressure than the second stream. In some of these embodiments, the first stream can be at a significantly higher pressure than the second stream. Accordingly, in these embodiments, the configuration of exit ports <NUM>, etc., can be to minimize flow turbulence, vortex shedding, and so forth (i.e., flow disturbances). Moreover, in various embodiments, the cross-sectional shape (i.e., profile) of probe shaft <NUM>, etc., can be configured to control and/or minimize flow disturbances. These various embodiments can be referred to as one or more flow enhancement features. In other embodiments, and/or during some operating conditions, a minimal pressure differential can exist between the first stream and the second stream. In some of these embodiments, the first stream and the second stream can have the same static pressure. In an exemplary embodiment, the first stream and the second stream can be driven by the same prime mover. Therefore, in some embodiments, channel flow F through temperature channel <NUM>, etc., is induced by the orientation of temperature orifice <NUM>, <NUM> and the orientation of exit port/ports <NUM>, etc. Accordingly, in these other embodiments, the configuration of exit ports <NUM>, etc., can be to promote the induction of channel flow F through temperature channel <NUM>, etc. For these reasons, the configuration of exit ports <NUM>, etc. with regard to size, placement, and/or number, can be to enhance channel flow F, and the exit ports can also be referred to as one or more flow enhancement features. While a gas turbine engine was depicted as an exemplary embodiment of temperature probe <NUM>, the scope of the present disclosure includes all embodiments where a flush-mount combined static pressure and temperature probe is used to measure a temperature or a total temperature of a first stream by inducing a flow of fluid from a first stream to a second stream. Each of the first and/or second streams can be gaseous or liquid. Air and exhaust gas are non-limiting examples of a gas; and fuel, oil, water, and aqueous solutions are non-limiting examples of a liquid.

A probe, comprising a probe head; a probe tip extending from the probe head and ending with a sensor face configured for fluidic communication with a first fluid stream; a pressure channel extending into the probe tip through the sensor face; a pressure sensor in configured to sense a pressure in the pressure channel; a temperature channel extending into the probe tip through the sensor face, the temperature channel including a temperature orifice disposed on the sensor face and at least one exit port distal from the sensor face; and a temperature sensor configured to sense a temperature in the temperature channel; wherein: the temperature channel extends parallel to the pressure channel; the temperature channel is fluidly separate from the pressure channel; the temperature channel is configured to channel a fluid flow from the temperature orifice to the at least one exit port; and the at least one exit port is configured to discharge the fluid flow into a second fluid stream.

The probe of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
A further embodiment of the foregoing probe, wherein: the second fluid stream defines a second fluid stream direction; and at least one exit port establishes an exit flow direction that is perpendicular to the second fluid stream direction.

A further embodiment of the foregoing probe, comprising two exit ports, one on an opposite side of the temperature channel from the other.

A further embodiment of the foregoing probe, wherein the pressure sensor is a static pressure sensor.

A further embodiment of the foregoing probe, wherein the temperature sensor is a total temperature sensor.

A further embodiment of the foregoing probe, further comprising a probe shaft, the probe shaft disposed between the sensor face and the probe head, wherein the at least one exit ports are disposed on the probe shaft.

A further embodiment of the foregoing probe, wherein: the probe shaft defines a probe shaft cross-sectional shape; and the probe shaft cross-sectional shape is circular.

A further embodiment of the foregoing probe, wherein: the probe shaft defines a probe shaft cross-sectional shape; the probe shaft cross-sectional shape is non-circular, defining a major width and a minor width; and the major width defines a major axis that is parallel to the second fluid stream direction.

A further embodiment of the foregoing probe, wherein the probe shaft cross-sectional shape is an ellipse, oval, airfoil, or teardrop shape.

A further embodiment of the foregoing probe, wherein the at least one exit port is configured to create a negative pressure on the temperature channel with respect to the temperature orifice, thereby inducing the fluid flow from the temperature orifice to the at least one exit port.

A further embodiment of the foregoing probe, wherein the first fluid stream is at a pressure greater than the second airflow stream.

A further embodiment of the foregoing probe, wherein: the first fluid stream is air; the second fluid stream is air; and the probe is configured to measure a static pressure and a total temperature in a primary airstream in a gas turbine engine.

A further embodiment of the foregoing probe, further comprising a gas turbine engine extending along an axis comprising: a fan section comprising a plurality of rotor cascades and a plurality of stator cascades; a compressor section downstream of the fan section; a combustor section downstream of the compressor section; and a turbine section downstream of the combustor section, the turbine section being connected to the compressor and/or fan section; wherein the probe is disposed on the compressor and/or fan section and is configured to sense a pressure and a total temperature of a first airflow stream.

A gas turbine engine extending along an axis comprising: a fan section comprising a plurality of rotor cascades and a plurality of stator cascades; a splitter downstream of the fan section, the splitter including inner side, an outer side, and an inside surface; a compressor section downstream of the fan section; a combustor section downstream of the compressor section; a turbine section downstream of the combustor section, the turbine section being connected to the compressor and/or fan sections; and a probe assembly, disposed on the compressor and/or fan section and configured to sense a pressure and a total temperature of a first airflow stream, the probe assembly comprising: a probe head; a probe tip extending from the probe head and ending with a sensor face configured for fluidic communication with a first fluid stream; a pressure channel extending into the probe tip through the sensor face; a pressure sensor configured to sense the pressure in the pressure channel; a temperature channel extending into the probe tip through the sensor face, the temperature channel including a temperature orifice disposed on the sensor face and at least one exit port distal from the sensor face; and a temperature sensor configured to sense the temperature in the temperature channel; wherein: the temperature channel extends parallel to the pressure channel; the temperature channel is fluidly separate from the pressure channel; the temperature channel is configured to channel air from the temperature orifice to the at least one exit port; and the at least one exit port is configured to discharge the airflow into a second airstream.

The gas turbine engine of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
A further embodiment of the foregoing gas turbine engine, wherein the pressure sensor is a static pressure sensor.

A further embodiment of the foregoing gas turbine engine, wherein the sensor face offset no more than <NUM> (<NUM> inch) from the inside surface of the splitter.

A further embodiment of the foregoing gas turbine engine, wherein the temperature channel includes an outlet positioned inside of the splitter.

A further embodiment of the foregoing gas turbine engine, wherein the temperature channel includes an outlet positioned outside of the splitter.

A further embodiment of the foregoing gas turbine engine, wherein a center of the temperature channel at the sensor face is in substantially the same axial position as a center of the pressure channel at the sensor face.

Claim 1:
A probe comprising:
a probe head (<NUM>);
a probe tip (<NUM>) extending from the probe head and ending with a sensor face (<NUM>) configured for fluidic communication with a first fluid stream;
a pressure channel (<NUM>) extending into the probe tip through the sensor face;
a pressure sensor (<NUM>) configured to sense a pressure in the pressure channel;
a temperature channel (<NUM>) extending into the probe tip through the sensor face, the temperature channel including a temperature orifice (<NUM>) disposed on the sensor face and at least one exit port (<NUM>) distal from the sensor face configured to discharge the fluid flow into a second fluid stream;
a temperature sensor (<NUM>) configured to sense a temperature in the temperature channel;
a probe shaft (<NUM>) disposed between the sensor face and the probe head;
the probe shaft (<NUM>) defines a probe shaft cross-sectional shape; characterized in that:
the probe shaft cross-sectional shape is non-circular, defining a major width and a minor width; and
the major width defines a major axis that is parallel to the second fluid stream direction;
wherein:
the temperature channel extends parallel to the pressure channel;
the temperature channel is fluidly separate from the pressure channel;
the temperature channel is configured to channel a fluid flow from the temperature orifice to the at least one exit port; and
the at least one exit ports are disposed on the probe shaft (<NUM>);
the probe shaft cross-sectional shape is an ellipse, oval, airfoil, or teardrop shape; and
wherein:
the second fluid stream defines a second fluid stream direction; and
the at least one exit port (<NUM>) establishes an exit flow direction that is perpendicular to the second fluid stream direction.