1. An oscillator coupling system, comprising:
a plurality of oscillating members;
at least a first delay member connecting at least two of the oscillating members; and
at least a second delay member for connection with the two oscillating members and introducing a phase or time delay parameter at least several times larger than that of the first delay member so as to be coupled to the two oscillating members having correlated phase or frequency noise suppression and reduce noise autocorrelation of the oscillator coupling system, thereby reducing noise by at least several dB to several dozens dB during system operation, wherein the second delay member is connected in series to a resistor so as to adjust a quality factor of the second delay member and strength of signals injected.
2. The oscillator coupling system of claim 1, wherein the first delay member is one of a signal line and an amplifier.
3. The oscillator coupling system of claim 2, wherein the signal line is one selected from the group consisting of a cable, a flat cable, a conductive line, and an electric transmission line.
4. The oscillator coupling system of claim 2, wherein the amplifier comprises at least one of a unidirectional amplifier and a bidirectional amplifier.
5. The oscillator coupling system of claim 1, wherein the second delay member is one of a phase delay member and a time delay member.
6. The oscillator coupling system of claim 5, wherein the phase delay member comprises one selected from the group consisting of an adjustable RLC circuit element, a delay signal line, a delay IC, and an amplifier.
7. The oscillator coupling system of claim 5, wherein the time delay member comprises one selected from the group consisting of a signal line, an adjustable RLC circuit element, a delay signal line, a delay IC, and an amplifier.
8. The oscillator coupling system of claim 7, wherein the signal line comprises one selected from the group consisting of a cable, a flat cable, a conductive line, and an electric transmission line.
9. The oscillator coupling system of claim 6, wherein the amplifier comprises at least one of a unidirectional amplifier and a bidirectional amplifier.
10. The oscillator coupling system of claim 7, wherein the amplifier comprises at least one of a unidirectional amplifier and a bidirectional amplifier.
11. The oscillator coupling system of claim 1, wherein the second delay member comprises a capacitor for adjusting the phase or time delay parameter of the second delay member.
12. The oscillator coupling system of claim 11, wherein the capacitor is an adjustable capacitor.
13. An oscillator coupling system, comprising:
a plurality of oscillating members;
at least a first delay member connecting at least two of the oscillating members; and
at least a second delay member for connection with the two oscillating members and introducing a phase or time delay parameter at least several times larger than that of the first delay member so as to be coupled to the two oscillating members having correlated phase or frequency noise suppression and reduce noise autocorrelation of the oscillator coupling system, thereby reducing noise by at least several dB to several dozens dB during system operation, wherein the second delay member comprises a capacitor for adjusting the phase or time delay parameter of the second delay member.
14. The oscillator coupling system of claim 13, wherein the capacitor is an adjustable capacitor.
15. The oscillator coupling system of claim 13, wherein the second delay member is connected in series to a resistor so as to adjust a quality factor of the second delay member and strength of signals injected.
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 system, comprising:
a gas turbine engine, comprising:
a combustion section;
a turbine section coupled to the combustion section, wherein the turbine section comprises a turbine stage having a plurality of turbine blades, each blade of the plurality of turbine blades having a blade end at a first end and a second end coupled to a rotor, and a stationary shroud disposed about the plurality of turbine blades that defines a clearance between each blade end of the plurality of turbine blades and an innermost surface of the stationary shroud that is disposed at an oblique angle relative to a rotational axis of the plurality of turbine blades; and
a diffuser section coupled to the turbine section, wherein the diffuser section comprises an outer wall defining an expanding flow path downstream from the plurality of turbine blades, the outer wall comprises a first wall portion that contacts and extends from the stationary shroud, the first wall portion having a first angle relative to the rotational axis of the plurality of turbine blades, the first angle is between 16 and 40 degrees, and when over tip leakage flow flows through the clearance between each blade end and the innermost surface of the stationary shroud, the over tip leakage flow energizes and maintains a boundary layer along the outer wall.
2. The system of claim 1, wherein the outer wall comprises a second wall portion downstream from and contacting the first wall portion, the second wall portion has a second angle relative to the rotational axis of the plurality of turbine blades, and the second angle is between 6 and 15 degrees.
3. The system of claim 2, wherein the first angle is between 20and 30 degrees.
4. The system of claim 1, wherein the clearance enables the over tip leakage flow to increase a radial flow velocity in the diffuser section to reduce flow separation along the outer wall.
5. The system of claim 1, wherein the clearance is between 90 and 150 mils.
6. The system of claim 1, wherein the diffuser section has a length and the gas turbine engine has a total length, and the length is less than 15percent of the total length.
7. A system, comprising:
a rotary section comprising a plurality of blades, each blade of the plurality of blades having a blade end at a first end and a second end coupled to a rotor, and a stationary shroud disposed about the plurality of blades that defines a clearance between each blade end of the plurality of blades and an innermost surface of the stationary shroud that is disposed at an oblique angle relative to a rotational axis of the plurality of blades; and
a diffuser section comprising an outer wall defining an expanding flow path downstream from the plurality of blades, wherein the outer wall comprises a first wall portion that contacts and extends from the stationary shroud, the first wall portion having a first angle relative to the rotational axis of the plurality of blades, the first angle is between 16 and 40 degrees, and when over tip leakage flow flows through the clearance between each blade end and the innermost surface of the stationary shroud, the over tip leakage flow energizes and maintains a boundary layer along the outer wall.
8. The system of claim 7, wherein the rotary section comprises a turbine section.
9. The system of claim 7, wherein the outer wall comprises a second wall portion downstream from and contacting the first wall portion, the second wall portion has a second angle relative to the rotational axis of the plurality of blades, and the second angle is between 6 and 15 degrees.
10. The system of claim 9, wherein the first angle is between 21 and 23 degrees, the second angle is between 7 and 9 degrees.
11. The system of claim 7, wherein, the clearance enables the over tip leakage flow to increase a radial flow velocity in the diffuser section to substantially reduce or eliminate flow separation along the outer wall.
12. A method, comprising:
enabling an over tip leakage flow to pass through a clearance between each blade end of a plurality of turbine blades of a turbine stage and an innermost surface of a stationary shroud that is disposed at an oblique angle relative to a rotational axis of the plurality of turbine blades;
radially expanding a flow from the plurality of turbine blades in a downstream direction through a first portion of a wall of a turbine diffuser that contacts and extends from the stationary shroud, the first wall portion having a first angle relative to the rotational axis of the plurality of turbine blades between 16 and 40 degrees; and
energizing and maintaining a boundary layer along the first portion of the wall of the turbine diffuser with the over tip leakage flow.
13. The method of claim 12, wherein the first angle is between 20 and 30 degrees.
14. The method of claim 12, comprising radially expanding the flow from the plurality of turbine blades from the first portion of the wall in the downstream direction through a second portion of the wall contacting the first wall portion and having a second angle relative to the rotational axis of the plurality of turbine blades between 6 and 15 degrees.
15. The method of claim 12, comprising diffusing an exhaust flow from the turbine stage through the turbine diffuser over a length that is less than 15 percent of a total length of a turbine engine having the turbine stage and the turbine diffuser.