# US 2015/0143797 A1 · Turbopump

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- Number: US 2015/0143797 A1
- Document ID: US20150143797A1
- Status: Published application
- Kind: A1
- Application number: 14/408,357
- Filed: 2013-06-14
- Published: 2015-05-28
- Earliest claimed: 2012-06-25
- Assignees: Snecma
- Applicants: Snecma
- Inventors: Gaelle Le Bouar; Richard Petit
- Web page: https://patentgrep.com/patent/US20150143797A1

## CPC

- F02K 9/46: using pumps
- F02K 9/48: driven by a gas turbine fed by propellant combustion gases {or fed by vaporized propellants or other gases}
- F02K 9/563: {of propellant feed pumps}
- F02K 9/64: having cooling arrangements
- F05D 2270/051: Thrust
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A feed method for feeding reaction engines including off-loading a secondary flow of a first propellant downstream from a first pump but upstream from a first turbine that is driven by expansion of the first propellant and that drives at least the first pump. The off-loading is controlled in such a manner as to achieve equilibrium between power generated by the first turbine and power consumed by the first pump, thereby stopping a rise in speed of the first turbine and the first pump at a predetermined speed lower than a nominal speed.

## Claims

### Claim at position 1

1-10. (canceled)

### Claim at position 2

11: A feed method for feeding at least one combustion chamber with at least a first propellant, the method comprising:
pumping a main flow and a secondary flow of the first propellant by a first pump;
heating at least the main flow of the first propellant in a heat exchanger downstream from the first pump;
expanding at least a portion of the main flow of the first propellant, after the heating, in a first turbine driving the first pump;
injecting the main flow of the first propellant downstream from the first turbine into the at least one combustion chamber; and
off-loading the secondary flow of the first propellant downstream from the first pump but upstream from the first turbine, the off-loading being controlled to achieve equilibrium between power generated by the first turbine and power consumed by the first pump, thereby stopping a rise in speed of the first turbine and the first pump at a predetermined speed lower than a nominal speed.

### Claim at position 3 (depends on 11)

12: A feed method according to claim 11, wherein the off-loading is performed between the first pump and the heat exchanger.

### Claim at position 4 (depends on 12)

13: A feed method according to claim 12, wherein the off-loading is performed via a valve for purging the first propellant.

### Claim at position 5 (depends on 11)

14: A feed method according to claim 11, wherein the off-loading is performed between the heat exchanger and the first turbine.

### Claim at position 6 (depends on 11)

15: A feed method according to claim 11, wherein the heat exchanger heats at least the main flow of the first propellant with heat generated in the combustion chamber.

### Claim at position 7 (depends on 11)

16: A feed method according to claim 11, wherein at least a portion of the main flow of the first propellant can bypass at least the first turbine via a first bypass passage fitted with a first bypass valve.

### Claim at position 8 (depends on 11)

17: A feed method according to claim 11, further comprising pumping a flow of a second propellant by a second pump and injecting at least a portion of this flow of the second propellant into the at least one combustion chamber.

### Claim at position 9 (depends on 17)

18: A feed method according to claim 17, further comprising expanding at least a portion of the main flow of the first propellant in a second turbine driving the second pump.

### Claim at position 10 (depends on 18)

19: A feed method according to claim 18, wherein at least a portion of the main flow of the first propellant can bypass at least the second turbine via a second bypass passage fitted with a second bypass valve.

### Claim at position 11 (depends on 18)

20: A feed method according to claim 18, wherein the second turbine is situated downstream from the first turbine.