Turbine, for a liquid-propellant rocket engine mainly

Details Turbine, for a liquid-propellant rocket engine mainly Turbine, for a liquid-propellant rocket engine mainly

1999-09-09

2001-11-27

Freay, Charles G. (Department: 3746)

Power plants

Reaction motor

Liquid oxidizer

C415S116000

Reexamination Certificate

active

06321528

ABSTRACT:

FIELD OF THE INVENTION
The invention relates to the field of power machine-building and may be used in turbines designed for liquid-propellant rocket engines (LRE).
BACKGROUND OF THE INVENTION
A turbine comprising a casing with a working chamber, a propellant feed passage and a cooling space communicating with cooling fluid feed passages, a turbine-wheel with a shroud located inside the working chamber, and an annular cooling space with cooling fluid feed passages, both located inside the casing, is known in the prior art (SU Inventor's Certificate, No. 1188337, Int. Cl F01D 11/10, 1985).
Disclosed in SU Inventor's Certificate No. 1537840 (Int. Cl. F01D 5/08, 1990) is another turbine comprising a casing provided with a cooling fluid feed passage communicating with an annular space used to feed a cooling fluid onto a turbine wheel.
A problem with the above turbines is the possibility of ignition when operating with active oxidizing gaseous fluids.
Still another conventional turbine comprises a casing with a working chamber, a propellant feed passage and a cooling space communicating with cooling fluid feed passages, a turbine wheel located in the working chamber and means for feeding a cooling fluid onto the turbine wheel, said means for feeding a cooling fluid being located in the end part of the working chamber on the side of the propellant feed passage and made as an annular chamber communicating with annular slots (U.S. Pat. No. 3,883,263, U.S. Cl. 415-116, 1975).
The above turbine is designed for transport engines However, in this case it is difficult to ensure the reliable operation of the turbine from the point of view of the ignition danger while using the widely-used materials when a high-temperature oxidizing fluid is used as a propellant, as takes place in some modern high-power LRE.
SUMMARY OF THE INVENTION
It is an object of the invention to prevent emergency situations and improve the operation reliability in a turbine in which a high-temperature oxidizing gas is used as a propellant.
The improved reliability is to be provided by means of preventing the ignition in the inner space of the turbine at the operation on an oxidizing gas, thereby increasing turbine lifetime.
The above object is achieved in a conventional turbine comprising a casing enclosing a working chamber, a propellant feed passage communicating with the working chamber, a cooling space, and a cooling fluid feed passage communicating with the cooling space, a turbine wheel located in the working chamber, means for feeding a cooling fluid onto the turbine wheel, said means being located in an end part of the working chamber on the side of the propellant feed passage and made as an annular chamber communicating with an annular slot provided in the casing and communicating with the cooling fluid feed passage, wherein in accordance with the invention the turbine wheel comprises a shroud, a bush made of a material, the thermal conductivity of which is higher than that of a material of the casing, is located coaxially to the turbine wheel, the bush being fastened in the casing to define a cooling space located above an outer surface of the bush, and having a length longer than that of the turbine wheel, the bush being mounted so that to bulge out of the turbine wheel towards the propellant feed passage, outer surfaces of the annular chamber and the annular slot of the means for feeding the cooling fluid onto the turbine-wheel being formed by an inner surface of the bulging out part of the bush.
Further embodiments of the invention are possible, in which it is advisable that the turbine further included a spacer made of a material with a higher thermal conductivity than that of the casing material, and mounted in the casing on the side of the propellant feed passage, an inner surface of the annular slot in the means for feeding a cooling fluid onto the turbine wheel can be formed by an outer surface of the spacer, and the bush can be made to consist of two parts located in the casing and made of bronze.


REFERENCES:
patent: 3883263 (1975-05-01), Mai
patent: 3943706 (1976-03-01), Grafwallner et al.
patent: 4073138 (1978-02-01), Beichel
patent: 5953900 (1999-09-01), Bannister et al.
patent: 1188337 (1985-10-01), None
patent: 1537840 (1990-01-01), None

Affiliated with

Also associated with

Rating

Turbine, for a liquid-propellant rocket engine mainly does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Turbine, for a liquid-propellant rocket engine mainly, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Turbine, for a liquid-propellant rocket engine mainly will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-2594740