1. An electronic device that autonomously adjusts at least one operating parameter of a haptic device, the electronic device comprising:
a haptic device;
a sensor configured to monitor the haptic device during operation of the haptic device and generate a measured signal;
a feedback loop comprising:
a filter coupled to the sensor and operative to filter the measured signal, thereby generating a filtered measured signal; and
an error detector coupled to the filter, wherein the error detector is configured to compare the filtered measured signal with a target signal to generate an error signal; and
a controller configured to receive the error signal and adjust a control signal in response to the error signal to achieve a desired operational parameter.
2. The electronic device of claim 1, wherein the sensor is an accelerometer.
3. The electronic device of claim 2, wherein values from the accelerometer are iteratively used by the electronic device to adjust the control signal.
4. The electronic device of claim 3, wherein the control signal is a pulse width modulation signal.
5. The electronic device of claim 1, the electronic device is a phone and the adjustment of the control signal occurs within an integer number of rings of the phone.
6. The electronic device of claim 1, wherein the haptic device is a vibrating device.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A gas turbine engine, comprising:
a compressor having an impeller;
a diffuser having a plurality of diffuser vanes;
wherein the impeller is a centrifugal impeller, and wherein the diffuser is a radial diffuser;
wherein the diffuser forms a flowpath downstream of the impeller;
wherein the diffuser vanes extend across the flowpath; and
wherein at least one of the diffuser vanes has a first opening extending through the diffuser vanes and across the flowpath;
a combustor in fluid communication with the compressor;
a turbine in fluid communication with the combustor; and
a secondary flow circuit operative to deliver secondary air flow to the impeller for controlling a temperature of a portion of the impeller, wherein the secondary air flow is delivered to the impeller from across the flowpath through the first opening; and
one or more walls defining a cavity separate from the flowpath, the one or more walls further having an opening therein configured to supply the secondary air flow from the cavity to at least one diffuser vane, wherein the impeller includes a plurality of blades and a back face opposite the plurality of blades, further comprising a static structure spaced apart from the back face and configured to direct the secondary air flow from a radially outer tip portion of the impeller radially inward along the back face of the impeller.
2. The gas turbine engine of claim 1, wherein the static structure is configured to direct the secondary air flow from the first opening to the back face of the impeller.
3. The gas turbine engine of claim 1, wherein the static structure includes a second opening configured to direct the secondary air flow from the first opening to the tip portion of the impeller.
4. The gas turbine engine of claim 1, wherein the one or more walls includes a first wall coupled to the diffuser, the first wall having the opening therein configured to supply the secondary air flow to the at least one diffuser vane from the cavity adjacent to the first wall.
5. The gas turbine engine of claim 4, wherein the first wall is a load bearing structure of the gas turbine engine.
6. The gas turbine engine of claim 4, wherein the one or more walls includes a second wall operative to form the cavity in conjunction with the first wall, wherein the first wall and the second wall are configured to support diffuser loads.
7. The gas turbine engine of claim 6, wherein the one or more walls includes an engine case, wherein the first wall and the second wall are coupled to the engine case; and wherein the engine case, the first wall and the second wall form the cavity.
8. A gas turbine engine, comprising:
a centrifugal compressor having an impeller and an impeller configured to generate a pressurized air flow;
a flowpath structure configured to form a flowpath downstream and radially outward of the impeller of the compressor and receive the pressurized air flow,
wherein the flowpath structure includes a stationary structure extending across the flowpath and having a transfer opening extending therethrough and across the flowpath;
a source of secondary air flow disposed on one side of the flowpath; and
a secondary flow circuit operative to deliver a secondary air flow to the impeller for controlling a temperature of a portion of the impeller,
wherein the secondary air flow is delivered to the impeller across the flowpath through the transfer opening; and
a first static structure coupled to the stationary structure and having a supply opening therein configured to supply the secondary air flow to the transfer opening, wherein the impeller includes a plurality of blades and a back face opposite the plurality of blades, further comprising a second static structure configured to direct the secondary air flow from a radially outer tip portion of the impeller radially inward along the back face of the impeller.
9. The gas turbine engine of claim 8, wherein the second static structure is configured to direct the secondary air flow from the transfer opening to the back face of the impeller.
10. The gas turbine engine of claim 9, further comprising a flow discourager between the second static structure and the impeller, wherein the flow discourager is configured to reduce a flow rate of the secondary air flow exiting the back face of the impeller.
11. The gas turbine engine of claim 10, wherein the flow discourager is a labyrinth seal.
12. The gas turbine engine of claim 8, further comprising a distribution channel fluidly coupling the supply opening with the transfer opening.
13. The gas turbine engine of claim 8, further comprising a turbine, wherein the secondary air flow is delivered to the turbine after acting on the impeller.