Jet engine booster structure

Details Jet engine booster structure Jet engine booster structure

1999-04-26

2002-02-26

Look, Edward K. (Department: 3745)

Rotary kinetic fluid motors or pumps

Working fluid passage or distributing means associated with...

Plural rigidly related blade sets

C415S914000, C416S19800R, C416S20000R

Reexamination Certificate

active

06350103

ABSTRACT:

BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to the booster structure of a jet engine. More specifically, the present invention relates to a jet engine booster structure having an improved pressure ratio in a single stage.
2. Description of the Related Art
In the prior art, there has been provided a booster
2
′ downstream of a fan
1
in order to enhance the performance of a high bypass engine E′, as shown in FIG.
11
.
As shown in
FIG. 11
, however, the booster
2
′ is provided on the same shaft
3
′ as the fan
1
and the number of revolutions of the booster
2
′ is the same as that of the fan
1
, whereby the circumferential speed of the moving blade
4
of the booster
2
′ is, therefore, limited by that of the fan
1
. Due to this, the circumferential speed of the moving blade
4
is extremely lower than a desired speed, so that a pressure ratio in a single stage becomes quite low. This results in a problem that the booster
2
′ must consist of many stages so as to ensure a desired pressure ratio. Also, if the number of stages of the booster
2
′ increases, the entire length of a compressor increases, resulting in a problem that the weight of an engine E′ increases. Furthermore, an increase in weight causes various problems.
SUMMARY OF THE INVENTION
The present invention has been made in view of the problems according to the prior art and has an object to provide a booster structure capable of obtaining a desired pressure ratio with fewer stages.
The jet engine booster structure according to the present invention is characterized in that a moving blade of a booster is a boundary layer control tandem moving blade.
In the jet engine booster structure according to the present invention, it is preferable that the inflow angle with a tandem moving blade lattice is within a range of 50 degrees to 70 degrees and that the efflux angle from the tandem moving blade lattice is within a range of 0 degree to 45 degrees. In addition, it is preferable that the deflection angle by a stator blade is within a range of 0 degree to 45 degrees.
Since the moving blade of the booster is the tandem moving blade in the booster structure according to the present invention, a pressure increase in a single stage is large and, therefore, a desired pressure increase can be attained with fewer stages.
Now, description will be given based on the mode of working the present invention with reference to the accompanying drawings. The present invention should, however, not be limited to the mode described herein.


REFERENCES:
patent: 3112866 (1963-12-01), Fortescue
patent: 3937592 (1976-02-01), Bammert
patent: 4859145 (1989-08-01), Sidransky
patent: 573799 (1933-03-01), None
patent: 3924829 (1991-02-01), None
patent: 0 823 540 (1998-02-01), None
patent: 10-54301 (1998-02-01), None

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