Gas turbine engine lubrication system and apparatus with boost pump system
A lubrication system for a gas turbine engine is provided. The lubrication system includes a supply source of a fluid lubricant, a main supply pump, and a boost pump system. The main supply pump has an MSP fluid flow inlet port and an MSP fluid flow exit port. The main supply pump is configured to receive a source fluid lubricant flow at a first pressure, and configured to produce a supply fluid flow at a second pressure. The second pressure is greater than the first pressure. The boost pump system has a boost pump having a BP fluid flow inlet port, and a BP fluid flow exit port. The boost pump system is configured so that the boost pump selectively receives at least a portion of the supply fluid flow from the main supply pump at the BP fluid flow inlet port, and the boost pump is configured to produce a boost supply fluid flow at a third pressure at the BP fluid flow exit port, wherein the third pressure is greater than the second pressure.
1. A lubrication system for a gas turbine engine having a plurality of components,
the lubrication system comprising:
a supply source of a fluid lubricant;
a main supply pump including a first fluid flow inlet port and a first fluid flow exit port, the first fluid flow inlet port in fluid communication with the supply source, and the first fluid flow exit port in fluid communication with the plurality of engine components;
the main supply pump configured to receive a source fluid lubricant flow from the supply source at a first pressure at the first fluid flow inlet port, and the main supply pump configured to produce a supply fluid flow at a second pressure at the first fluid flow exit port, wherein the second pressure is greater than the first pressure; and
a boost pump system including a boost pump, the boost pump including a second fluid flow inlet port and a second fluid flow exit port, the second fluid flow inlet port in fluid communication with the supply source, and the second fluid flow exit port in selective fluid communication with at least one of the plurality of engine components;
the boost pump system configured to produce a boost supply fluid flow at a third pressure at the second fluid flow exit port, wherein the third pressure is greater than the second pressure, and the lubrication system configured to provide the boost supply fluid flow to at least one said component independently of the supply fluid flow.
2. The lubrication system of claim 1 , wherein the boost pump is driven by a mechanical power source.
3. The lubrication system of claim 2 , wherein, when the boost pump is in an active state, the boost pump is configured to continuously produce the boost supply fluid flow at the third pressure at the second fluid flow exit port.
4. The lubrication system of claim 3 , wherein the boost pump system includes a bypass valve; and
the boost pump system is configured to selectively direct at least a portion of boost supply fluid flow through the bypass valve and out of the boost pump system at a position upstream of the at least one of the plurality of engine components.
5. The lubrication system of claim 1 , wherein the boost pump is driven by an independent power source, the boost pump is selectively controllable to an active state or an inactive state;
the boost pump is configured to continuously produce the boost supply fluid flow at the third pressure at the second fluid flow exit port in the active state; and
the boost pump is non-operational in the inactive state.
6. The lubrication system of claim 5 , wherein the boost pump is at least one of pneumatically, electrically, or hydraulically powered.
7. A gas turbine engine, comprising:
a shaft;
a bearing compartment configured to support the shaft, the bearing compartment including a bearing and a fluid damped structure; and
a lubrication system comprising:
a supply source of a fluid lubricant;
a main supply pump including a first fluid flow inlet port and a first fluid flow exit port, the first fluid flow inlet port in fluid communication with the supply source, and the fluid flow exit port in fluid communication with the bearing compartment;
the main supply pump configured to receive a source fluid lubricant flow from the supply source at a first pressure at the first fluid flow inlet port, and the main supply pump configured to produce a supply fluid flow at a second pressure at the first fluid flow exit port, wherein the second pressure is greater than the first pressure; and
a boost pump system comprising a boost pump, the boost pump including a second fluid flow inlet port and a second fluid flow exit port, the second fluid flow inlet port in fluid communication with the supply source, and the second fluid flow exit port in fluid communication with the fluid damped structure of the bearing compartment;
the boost pump configured to produce a boost supply fluid flow at a third pressure at the second fluid flow exit port, wherein the third pressure is greater than the second pressure, and the lubrication system configured to provide the boost supply fluid flow to at least one said component independently of the supply fluid flow.
8. The gas turbine engine of claim 7 , wherein the boost pump is driven by a mechanical power source directly or indirectly in communication with the shaft.
9. The gas turbine engine of claim 8 , wherein, when the boost pump is in an active state, the boost pump is configured to continuously produce the boost supply fluid flow at the third pressure at the second fluid flow exit port.
10. The gas turbine engine of claim 9 , wherein the boost pump system includes a bypass valve; and
the boost pump is configured to selectively direct at least a portion of boost supply fluid flow through the bypass valve and out of the boost pump system at a position upstream of the bearing compartment.
11. The gas turbine engine of claim 7 , wherein the boost pump is driven by an independent power source, and the boost pump is selectively controllable to an active state where the boost pump continuously produces the boost supply fluid flow at the third pressure at the second fluid flow exit port, or to an inactive state where the boost pump is not operating.
12. The gas turbine engine of claim 11 , wherein the boost pump is at least one of pneumatically, electrically, or hydraulically powered.
13. The gas turbine engine of claim 7 , wherein the fluid damped structure is disposed within the bearing compartment and configured to permit radial movement of the bearing within the bearing compartment.